| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244001000 | Lightning arresters and static eliminators | 62 |
| 20080217471 | INTELLIGENT AIRCRAFT SECONDARY POWER DISTRIBUTION SYSTEM THAT FACILITATES CONDITION BASED MAINTENANCE - An electrical power distribution system comprises a solid state power controller in communication with an aircraft system main data bus via a gateway module and a condition based maintenance module in communication with the solid state power controller via a communication network distinct from the main data bus. A method of load/feeder health assessment for an electrical power distribution system includes applying a controlled excitation to a load; sampling information from the load/feeder system for the load; characterizing a normal behavior of the load/feeder system for the load; determining if the load characteristics are within the normal behavior profile for the load; and shutting down power to the load if load characteristics are not within the profile when immediate action is indicated or generating a health message for the load when immediate action is not required. | 09-11-2008 |
| 20080217472 | ROCKET-POWERED VEHICLE RACING REALITY SYSTEM - An aerial vehicle race and reality system for entertaining spectators wherein computer-generated images are optionally provided to at-least partially define a race-course. | 09-11-2008 |
| 20080217473 | ROCKET-POWERED VEHICLE RACING COMPETITION - A method for racing rocket-powered vehicles directly against one another is provided in which a first rocket-powered vehicle simultaneously races against a second rocket-powered vehicle to be the first to complete a race course. The method may include the first and second rocket-powered vehicles performing a pre-determined maneuver while proximate a group of spectators, and/or the rocket-powered vehicles strategically performing the steps of gliding and boosting the flight of their rocket-powered vehicle in accordance with a pre-determined maximum fuel criteria. The method further may include permitting spectator interaction with participants of the racing competition and enabling spectators to compete with actual participants via virtual vehicles. The method may also include the rocket-powered vehicles performing a refueling operation. The method may further include providing audible or visual identifiers of the vehicles. In addition, the method may include providing safety data to ensure safe separation between competing vehicles. | 09-11-2008 |
| 20080258006 | High altitude structures control system and related methods - A system and method is described generally for providing a high altitude structure including an elongated structure extending substantially skyward from the ground. The elongated structure at least partially supported by buoyancy effects. The system and method also include a gas having a density that is less dense than that of the atmosphere outside of the elongated structure; the gas is disposed in one or more voids of the elongated structure. The system and method further include at least one control device coupled to the elongated structure and used to control the motion of the elongated structure, the control device not being directly coupled to the surface of the Earth. | 10-23-2008 |
| 20080272233 | Method and system for generating renewable energy - A method, system and apparatus for the generation of energy. The method system and apparatus can include one or more airships that collect solar energy and convert it into electricity. An array of airships may be used so as to increase the collection rates of solar energy. The array of airships may include an airship that receives and stores electricity from the other airships in the array. Additionally, the solar energy may be transmitted to a terrestrial collection and distribution station. | 11-06-2008 |
| 20090065638 | Apparatus for voice communication between persons inside and persons outside an aircraft - An apparatus for facilitating voice communication between persons outside an aircraft and persons inside an aircraft, is disclosed, comprising: an external control unit comprising: voice sensing means; transmitting means for transmitting voice information to persons in said aircraft; receiving means for receiving voice information from persons in said aircraft; and amplifying means for enabling said voice information to be heard; and an in-aircraft control unit comprising: voice sensing means; transmitting means for transmitting voice information to persons external to said aircraft; receiving means for receiving voice information from persons external to said aircraft; and amplifying means for enabling said voice information to be heard. | 03-12-2009 |
| 20090127386 | METHODS AND SYSTEMS FOR IMPROVING AIRCRAFT VISIBILITY - A method for improving the conspicuity of aircraft is described that includes determining onto which exposed portions of an aircraft surface a retro-reflective material is to be placed, and attaching the retro-reflective material to the exposed portions such that an observer of the retro-reflective material is provided with an indication of a size, location, and orientation of the aircraft. | 05-21-2009 |
| 20090173822 | Distributed infrared countermeasure installation for fixed wing aircraft - A distributed aircraft defense system involving infrared countermeasures is installed in a distributive fashion for commercial aircraft, typically fixed wing aircraft, in which maintenance downtime is minimized due to the ability to access, remove, test, fix and/or replace individual modules within the distributed system. | 07-09-2009 |
| 20090194634 | UNMANNED VEHICLE HAVING A CAMOUFLAGE APPARATUS - An unmanned vehicle has a camouflage apparatus which simulates a characteristic of an animal. This allows effective camouflage to be achieved despite the unmanned vehicle being clearly visible. | 08-06-2009 |
| 20090242695 | SECURING EMERGENCY AND SAFETY EQUIPMENT ON AIRCRAFT - An emergency equipment system comprising an elongate member, an emergency equipment package, and a cutter. The elongate member may have a first end and an angled end. The emergency equipment package may have a sleeve on one side capable of receiving the elongate member from the angled end. The cutter may be attached to a side of the elongate member and may be capable of cutting the sleeve. | 10-01-2009 |
| 20100001127 | METHOD FOR CONTROLLING THE INTERNAL PRESSURE IN AN AIRCRAFT - The present invention provides a method for controlling an internal pressure in an aircraft or spacecraft, the method comprising the following steps: detecting the internal pressure in the craft and an external pressure Pa outside of the craft and comparing said pressures with each other; and adjusting a flap of at least one outflow valve to a blade position, in which the flap directs air flowing past an outer surface of the craft into the craft to increase the internal pressure, if the external pressure exceeds the internal pressure by a predetermined value during the descent of the craft. The idea, on which the present invention is based, is to assign a double function to the outflow valve: during normal flight the positive pressure in the craft is relieved by means of the outflow valve. During a too steep descent or in case of failure of the air conditioner of the craft, the flap directs air into the craft and thus adapts the internal pressure to the external pressure as soon as it exceeds the internal pressure. Thus, a negative pressure relief valve is advantageously not required and a size thereof can be considerably reduced respectively. | 01-07-2010 |
| 20100019084 | Aerospace manufacturing system - An Aerospace Manufacturing System is disclosed, which comprises methods and apparatus for reducing the manufacturing costs in an aerospace product. In one embodiment, this method is accomplished by designing the aerospace product to use non-aerospace industry components and by maximizing the use of said plurality of readily commercially available, non-aerospace industry components. These commercially available, non-aerospace components are sometimes referred to by the term “commercial off the shelf” or “COTS” products. | 01-28-2010 |
| 20100025527 | SURGICALLY IMPLANTED MICRO-PLATFORMS AND MICROSYSTEMS IN ARTHROPODS AND METHODS BASED THEREON - A method is provided for producing an arthropod comprising introducing a microsystem such as a MEMS device into an immature arthropod under conditions that result in producing an adult arthropod with a functional microsystem permanently attached to its body. A method is also provided for producing a robotic apparatus. The method can comprise introducing a microsystem such as a MEMS device into an immature arthropod under conditions that result in producing a robotic apparatus with the microsystem permanently attached to the body of the adult arthropod. | 02-04-2010 |
| 20100224725 | System and method for powering an aircraft using radio frequency signals and feedback - A system and method are described for powering an aircraft using radio frequency (“RF”) signals. For example, a method according to one embodiment of the invention comprises: positioning an antenna array beneath or on the road surface of a roadway, the antenna array configured to transmit RF signals responsive to RF processing logic and/or circuitry; coupling a rectenna array to an aircraft, the rectenna array configured to receive the RF signals transmitted from the antenna array and to generate power from the RF signals; providing feedback signals from the aircraft to the RF processing logic and/or circuitry, the feedback signals including channel state information (CSI) defining a current state of the channels between the antenna array and the rectenna array, the RF processing logic and/or circuitry using the channel state information to adjust the RF signal transmissions from the antenna array to improve the efficiency of the power generated by the rectenna array; and using the power generated by the rectenna array to power the aircraft. | 09-09-2010 |
| 20100270427 | BIRD COLLISION PREVENTION DEVICE FOR AN AIRCRAFT - A bird collision prevention device with a plurality of circular interior support members with decreasing diameters concentrically disposed along an axis, a plurality of outer ribs welded tangentially to the circular interior support members forming a like conical shape mesh body, a plurality of bolts or latches securable to the circular interior support member with the largest diameter and the cowling, and wherein the mesh body is secured to the cowling of the turbine engine enabling a tapered end of the mesh body to extend away from the turbine engine. | 10-28-2010 |
| 20110180661 | Optically Reconfigurable Radio Frequency Antennas - Optically reconfigurable radio frequency antennas for use in aircraft systems and methods of its use are disclosed. In one embodiment, the antenna includes a surface-conformal reflector that includes optically addressable carbon nanotubes. The nanotubes can be combined with light-sensitive materials so that exposure to light of the correct wavelength will switch the nanotubes back and forth between a metallic and non-metallic state. The antenna has a transmitter that radiates a radio frequency signal in the direction of the surface illuminator and an addressable optical conductor to illuminate the nanotubes with one or more optical signals. When the domains are illuminated they switch portions of the carbon nanotubes between its non-metallic states and metallic states to reflect the radiated radio frequency signal. | 07-28-2011 |
| 20120138741 | Method And Device For Aiding The Localization Of An Aircraft Wreck Submerged In A Sea - Method and device for aiding the localization of an aircraft wreck submerged in a sea. | 06-07-2012 |
| 20130020435 | DATA ACQUISITION SYSTEM AND APPARATUS - A data acquisition system comprising: an aircraft ejectable seat; a flight data recorder removeably attached to the ejectable seat; a data connector in signal communication with the flight data recorder, and configured to removeably connect to an aircraft's data bus. A data acquisition apparatus comprising: a flight data recorder; a data connector in signal communication with the flight data recorder, and configured to removeably connect to an aircraft's data bus; and where the flight data recorder is configured to removeably attach to an ejectable aircraft seat. | 01-24-2013 |
| 20130206901 | SMALL ARMS CLASSIFICATION/IDENTIFICATION USING BURST ANALYSIS - Systems and methods are provided for differentiating weapon fire from targets on the ground to an aircraft such that appropriate countermeasures can be taken. A plurality of shots from a target on the ground is detected from a sensor in the aircraft. Shots belonging to a single burst are correlated. A firing characteristic of the plurality of shots in the burst is computed. A weapon type is determined for the plurality of shots based on the firing characteristic. | 08-15-2013 |
| 20130292512 | ENVIRONMENTAL SAMPLING WITH AN UNMANNED AERIAL VEHICLE - Environmental samples are collected and analyzed using an unmanned aerial vehicle (UAV). In some examples, the sample is drawn into engagement with a sensor onboard a UAV by the existing fluid flow generated by a rotor fan through a duct of a ducted fan of the UAV. The quality characteristics of the fluid sample may be physically or wirelessly delivered to a remote location. In some examples, samples are drawn into engagement with the sensor by a flexible tube that is attached to an outer surface of the UAV. The flexible tube may allow the UAV to precisely target and collect samples of dust and moisture and other materials from the ground over which the UAV operates. | 11-07-2013 |
| 20140014772 | Jet mobil flying machine - The Jet Mobil Flying Machines designed to mobilize individual(s) through the air perhaps through hydraulic, digital mechanism that propels one into air space . . . flying. It has a concept of light weightiness, yet effective—able to fly/transport at an amusement park, landing center or for private usage. This is an invention design for amusement parks and future air travel. It consists of a new jet Mobil, specific handle (house the control mechanism), magnetic disc, and track. On the new jet Mobil flying machine the panel would include all in a unit that i.e. required to make it fly (laser unit), a magnetic port pad Would consist of a field of energy whereby when connected to track and immediate suction process is able to attract it to the landing disc . . . This design should include the lightest materials created to develop a smooth style and intelligently operating Jet Mobil flying machine to travel from one port to another . . . | 01-16-2014 |
| 20140054414 | Cable Cutting Device for Aircraft - The invention disclosed relates to a cable-cutting device for cutting a cable under tension. The device is intended for use in conjunction with aircraft, particularly helicopters, to provide reasonable protection from cable strikes. The device includes a main body carrying in a bottom recess a pair of co-acting cable-cutting edges arranged at a suitable angle to produce a wedge-like mechanical advantage to at least partially cut a cable so that the cable will fail under moderate tension. The main body is formed of a composite material defined by a light weight foam central core and wrappings of carbon fiber fabric infused by a resin where the blades are molded into the walls of the recess. | 02-27-2014 |
| 20140061382 | Long and Short Range Storage and Transmission System on Aircraft Parts - According to one embodiment, an aircraft part storage system includes a first storage device and a second storage device. The first storage device is configured to be coupled to an aircraft part and operable to store and transmit a first set of information about the aircraft part. The second storage device is configured to be coupled to the same aircraft part and operable to store and transmit a second set of information about the aircraft part. The second storage device has a larger storage capacity than the first storage device but a shorter transmission range than the first storage device. | 03-06-2014 |
| 20140117154 | ROTORCRAFT FITTED WITH A MOUNTING STRUCTURE FOR JOINTLY MOUNTING A CONTROL PANEL AND AN AVIONICS RACK PREVIOUSLY FITTED WITH A UNITARY CABLING ASSEMBLY - A rotorcraft fitted with means for mounting at least one front avionics rack ( | 05-01-2014 |
| 20160375999 | UAV HAVING HERMETICALLY SEALED MODULARIZED COMPARTMENTS AND FLUID DRAIN PORTS - In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage. | 12-29-2016 |
| 20220135246 | SPARK CONTAINMENT CAP - A spark containment cap forms a sealed cavity around an end of a fastener protruding from a structure. The cap has a cap body defining an air cavity enclosing the end of the fastener. The cap body includes an annular base ( | 05-05-2022 |
| 20080251636 | AIRCRAFT THAT COMPRISES A STRUCTURE THAT ENSURES THE STRUCTURAL AND ELECTRICAL FUNCTIONS - An aircraft includes a structure with structural elements ( | 10-16-2008 |
| 20090050735 | SYSTEMS AND METHODS RELATED TO ELECTROMAGNETIC ENERGY DISSIPATION - Embodiments of the present invention relate generally to systems and methods related to electromagnetic energy dissipation, including the dissipation of static electricity. One aspect of the invention is directed toward an electromagnetic dissipation system that includes a conductive material, a protective element, and a base element. The conductive material is coupled between a portion of the outer surface of the protective element and a portion of the outer surface of the base element to form a modular dissipation system. Other aspects of the invention are directed toward a vehicle system that includes a receiving surface, a conductive element, and a protective element. The conductive element is (a) coupled between a portion of the receiving surface of the vehicle and a portion of the outer surface of the protective element, and/or (b) embedded in the portion of the receiving surface. | 02-26-2009 |
| 20090166468 | METHOD AND APPARATUS FOR SKIN MAPPING OF LIGHTNING DETECTION SYSTEM - A lightning strike to an aircraft causes problems in existing aircraft equipment. To offset the problem, weather equipment can be used, but the weather equipment is prone to noise interference with existing aircraft equipment. By effectively positioning the weather equipment, the present invention solves the noise interference problem. In particular, the process detects an environment event, using weather equipment, on the subject aircraft. Next, the system identifies an origination point of noise, resulting from the detected environment event, in internal aircraft equipment. After identifying the origination point of the noise, the system makes a measurement to determine if the noise is interfering with a signal of the internal aircraft equipment. If interference exists, an operator cancels the noise and adjusts the location of the weather equipment in an external surface of the subject aircraft in such a manner as to provide an interference free environment for the internal aircraft equipment. | 07-02-2009 |
| 20090184199 | Shielding arrangement for lines, in particular electrical lines, in aircraft - A shielding arrangement for the lightning protection of electrical lines and components in an aircraft includes a protected installation space for receiving the lines that is arranged in the region of a floor framework, at least one delimiting surface of the installation space being provided at least in certain regions with an electrically conductive shielding, the at least one delimiting surface of the installation space being formed with at least one floor panel and a further delimiting surface of the installation space being formed with at least one ceiling panel. | 07-23-2009 |
| 20090266935 | SHELL ARRANGEMENT AS WELL AS AIRCRAFT OR SPACECRAFT - The present invention provides a shell arrangement as well as an aircraft or spacecraft comprising such a shell arrangement. The shell arrangement comprises a first lightning conductor layer for conducting lightning energy and a fibre composite layer supporting the first lightning conductor layer. Furthermore, the shell arrangement comprises a first electrical connection for connecting a first electrical component with the first lightning conductor layer. The advantage resulting according to the invention is that the lightning conductor layer fulfils a double function: on the one hand it serves to conduct lightning energy and on the other hand it forms a portion of a circuit for operating the first electrical component. For this reason, the need for electrical wiring in the airplane is reduced, in turn resulting in a weight reduction for the aircraft or spacecraft. | 10-29-2009 |
| 20100001126 | COATING OF AN AIRCRAFT SEAT MOUNTING RAIL OR A AIRCRAFT SEAT STUD - A mounting rail that is designed for mounting installations in an aircraft, with the mounting rail being coated with a coating made of a coating material, wherein the coefficient of friction between the coating material and a material of an element to be mounted is lower than the coefficient of friction between a material from which the non-coated mounting rail is made and a material of an element to be mounted. The coating material may be provided with a conductive additive. | 01-07-2010 |
| 20100108804 | AIRCRAFT ASSEMBLY AND METHOD FOR MANUFACTURING THE SAME - An aircraft assembly having improved durability and capable of providing good lightning protection is provided. Provided is an aircraft assembly ( | 05-06-2010 |
| 20100213312 | Distributing Power in Systems Having a Composite Structure - Systems and methods to distribute power in a system having a composite structure are provided. A particular aircraft includes a fuselage having a composite skin. The composite skin includes a first resin and a plurality of fibers. The fuselage also includes an expanded conductive patch bonded to an interior surface of the composite skin by a second resin. The expanded conductive patch is in electrical contact with the plurality of fibers. The fuselage also includes a connector in electrical contact with the expanded conductive patch. | 08-26-2010 |
| 20100219287 | PROTECTION AGAINST DIRECT LIGHTNING STRIKES IN RIVETED AREAS OF CFRP PANELS - The invention relates to a metalization structure of aircraft panels and process for obtaining such structure, such that it comprise a structure of a panel ( | 09-02-2010 |
| 20100224724 | AIRCRAFT ASSEMBLY - Provided is an aircraft assembly equipped with a lightning protection structure that is not easily destroyed by lightning current and that is highly reliable. In an aircraft assembly including a skin ( | 09-09-2010 |
| 20100276536 | LIGHTNING PROTECTION SYSTEM AND AIRCRAFT COMPRISING SUCH A SYSTEM - An anti-lightning system for a composite structure having an external surface configured to be subjected to an air flow, the aforementioned system including at least one electrically conducting strip and fasteners attaching this strip to the aforementioned structure. According to the disclosed embodiments, with this structure including holes configured to accept the fastenings for the strip, at least some these fastenings comprise an attachment element that attaches the lightning to this structure. This attachment element is configured to be inserted in the hole with its upper part substantially flush with the external surface of the structure, this attachment element being in electrical contact with the electrically conducting strip. The electrically conducting strip is configured to be positioned on the opposite side of the structure to the external surface and electrically earthed. | 11-04-2010 |
| 20100320315 | LIGHTNING-PROTECTION FASTENER - Provided is a lightning-protection fastener that is capable of reliably preventing peeling off of an insulation layer during the operation of an aircraft and of improving the anti-lightning-strike capability and reliability. There is a lightning-protection fastener that fastens a skin of an aircraft and a structural member positioned inside the skin, in which an insulation layer is melt adhered so as to cover one end surface of a head portion and also to mechanically engage with a fastener-side engagement portion (engagement portion) formed on the end surface. | 12-23-2010 |
| 20110017867 | COMPOSITE MATERIALS - A composite material, the composite material comprising a prepreg, said prepreg comprising at least one polymeric resin and at least one conductive fibrous reinforcement, electrically conducting particles dispersed in the polymeric resin and a top layer of a metal-coated carbon fibre comprising a further resin component, wherein the metal comprises one or more metals selected from nickel, copper, gold, platinum, palladium, indium and silver. | 01-27-2011 |
| 20110049292 | LIGHTNING STRIKE PROTECTION - An aircraft component having an external surface includes an improved lightning strike protection surface film disposed on or proximate to the external surface. The surface film includes a preform that includes a substrate having a first areal weight density and a plurality of spaced carbon nanotubes grown on the substrate, the nanotubes having a second areal weight density. The sum of the first areal weight density and the second areal weight density is less than about 500 grams per square meter, and the preform has a surface resistance less than about 1 ohm/square. | 03-03-2011 |
| 20110073708 | Composite Barrel Sections for Aircraft Fuselages and Other Structures, and Methods and Systems for Manufacturing Such Barrel Sections - Composite sections for aircraft fuselages and methods and systems for manufacturing such sections are disclosed herein. A composite section configured in accordance with one embodiment of the invention includes a skin and at least first and second stiffeners. The skin can include a plurality of unidirectional fibers forming a continuous surface extending 360 degrees about an axis. The first stiffener can include a first flange portion bonded to an interior surface of the skin and a first raised portion projecting inwardly and away from the interior surface of the skin. The second stiffener can include a second flange portion bonded to the interior surface of the skin and a second raised portion projecting inwardly and away from the interior surface of the skin. A method for manufacturing a section of a fuselage in accordance with one embodiment of the invention includes positioning a plurality of uncured stiffeners on a mandrel assembly. The method can further include applying a plurality of fiber tows around the plurality of uncured stiffeners on the mandrel assembly. | 03-31-2011 |
| 20110226896 | LIGHTNING-RESISTANT FASTENER, CAP, FASTENER MEMBER, AND METHOD FOR ATTACHING LIGHTNING-RESISTANT FASTENER - A lightning-resistant fastener, a cap, a fastener member, and a method for attaching the lightning-resistant fastener are provided, which enhance workability and quality stability besides reliably securing an insulating property, and can lead to enhancement in safety of an airframe and reduction in manufacturing cost. A head portion | 09-22-2011 |
| 20110259999 | LIGHTNING PROTECTION ARRANGEMENT FOR AN ELECTRONIC UNIT - Lightning protection arrangement for diverting a current, caused by a lightning strike, from an electronic unit which is fitted to an aerodynamic fairing of an aircraft. The device comprises an electrically conductive mounting plate which is arranged on an outer side of a CFRP sandwich panel of the aerodynamic fairing. Furthermore, the device has an electrically conductive rear plate which is arranged on an inner side of the CFRP sandwich panel of the aerodynamic fairing and is connected electrically to the mounting plate. In this respect, a first group of attachment means provided for the electronic unit connects the electrical unit electrically to the rear plate. An electric current generated during a lightning strike is diverted with low resistance from the electrical unit via the rear plate and the mounting plate onto the fuselage of the aircraft. | 10-27-2011 |
| 20110284688 | ROTOR PROVIDED WITH A DEVICE FOR PROTECTING IT AGAINST LIGHTNING, AND AN AIRCRAFT PROVIDED WITH SUCH A ROTOR | 11-24-2011 |
| 20110315818 | Static Dissipative Fuel Tank Coatings and Methods - There is provided a method for mitigating static discharge in a fuel container. The method provides a static dissipative coating having a volume resistivity of 1.0×10 | 12-29-2011 |
| 20120043415 | BOND LEAD - A bonding lead comprising a core; and a sheath bonded to the core. The core comprises a substrate of fibres coated with nano-objects with at least one dimension between 1 nm and 200 nm. The nano-objects form a continuous electrically conductive network from one end of the bonding lead to the other with some of the nano-objects coating the fibres and others forming bridges between adjacent fibres. The nano-objects may be carbon nanotubes and the core may be woven or knitted. A conductive connector is provided at each end of the bonding lead, for instance a tab formed from an electrically conductive polymer. The lead can be used to dissipate static charge and/or lightning current between components, typically within an aircraft fuel tank. | 02-23-2012 |
| 20120074257 | LIGHTNING-RESISTANT FASTENER, CAP, AND METHOD OF MOUNTING LIGHTNING-RESISTANT FASTENER - There are provided a lightning-resistant fastener and a cap, which, while assuring sufficient insulation properties, provide improved workability and highly stable quality to thereby enable a reduction in the manufacturing cost of an airframe, and a method of mounting the lightning-resistant fastener. A hole | 03-29-2012 |
| 20120091269 | LIGHTNING STRIKE PROTECTION IN AIRCRAFT - Lightning strike protection in aircraft: the invention refers to a lightning strike protection system for fuel tank access covers ( | 04-19-2012 |
| 20120119022 | APPLICATION OF INSULATING COATING - Systems and methods for discontinuously applying an insulating primer to a carbon fiber reinforced plastic (CFRP) component are disclosed. In one embodiment, a method for mitigating electrical surface discharges from a CFRP component includes first applying an insulating primer to a metallic component. Next, an insulating primer is applied discontinuously to the CFRP component adjacent the metallic component. The discontinuous application of the insulating primer forms a primed portions and unprimed portions. The unprimed portions are configured to enable electrostatic dissipation. | 05-17-2012 |
| 20120126054 | LIGHTNING PROTECTION FOR COMPOSITE AIRCRAFT STRUCTURES - Lightning protection system ( | 05-24-2012 |
| 20120145825 | LIGHTNING AND CORROSION PROTECTION ARRANGEMENT IN AN AIRCRAFT STRUCTURAL COMPONENT - A lightning and corrosion protection arrangement for a joint between an outer metallic part ( | 06-14-2012 |
| 20120160960 | LIGHTNING-RESISTANT FASTENER - There is provided a lightning-resistant fastener that can secure sufficient lightning-resistance performance at low cost and realize efficiency of field work and improvement of reliability. An insulating coat film | 06-28-2012 |
| 20120181384 | DEVICE FOR PROTECTING PIPING FROM LIGHTNING - A device for protecting piping from lightning. The piping includes tubular metal sections connected to each other by connection parts, a first portion of the connection parts being plastic material parts and a second portion of the connection parts being metal parts. | 07-19-2012 |
| 20120292439 | ARTICLE WITH DE-ICING/ANTI-ICING FUNCTION - A structural article including an outer surface that serves as an aerodynamic surface when the structural article is subjected for an air stream. A resin matrix laminate includes an upper ply and a bottom ply. A heating element is arranged in contact with the bottom ply and coupled to a power supply unit in purpose to deice/anti-ice the outer surface. Each ply includes a thermally conductive filament structure having a filament orientation such that the prolongation of the filaments has an extension essentially perpendicular to the extension of the laminate. The thermally conductive filament structure of the upper ply is embedded in the upper ply in such way that at least a portion of the thermally conductive filament structure is exposed in the outer surface. | 11-22-2012 |
| 20130009001 | Electric Charge Dissipation System for Aircraft - A method and apparatus comprising a first composite layer and a second composite layer in which the second composite layer is associated with the first composite layer. The first composite layer and the second composite layer form a structure. The second composite layer has a conductivity configured to dissipate an electric charge on a surface of the structure and limit a flow of an electrical current in the second composite layer in which the electrical current is caused by an electromagnetic event. | 01-10-2013 |
| 20130015292 | Decorative Decal System for an AircraftAANM Zielinski; EdwardAACI KentAAST WAAACO USAAGP Zielinski; Edward Kent WA USAANM Iwamoto; James T.AACI RentonAAST WAAACO USAAGP Iwamoto; James T. Renton WA US - A method and apparatus comprising a layer of material having a decorative graphic and an electrically conductive material in the layer of material. The layer of material is configured to be attached to a surface of an aircraft. The electrically conductive material is configured to cause a current from an atmospheric electrostatic discharge contacting the layer of material to spread out in a desired amount within the layer of material. | 01-17-2013 |
| 20130043342 | MULTIFUNCTIONAL DE-ICING/ANTI-ICING SYSTEM - A de-icing/anti-icing system including at least two conductive structures embedded in an article that includes an outer surface designed as an aerodynamic surface. At least one of the conductive structures is arranged adjacent the outer surface. A control unit adapted to control the energy supply to the conductive structures for generating heat to the outer surface. A first of the conductive structures includes a first conductive nano structure and a second of the conductive structures includes a second conductive nano structure. A conductive property of the first of the conductive structures differs from a conductive property of the second of the conductive structures. The first conductive nano structure serves as a heating conductor and the second conductive nano structure serves as a heating element. The first and second conductive nano structures are embedded in a common plane of a resin layer forming the outer surface. | 02-21-2013 |
| 20130087655 | Precipitation Static Charge Drain System For An Aircraft Window - A static charge drain system for an aircraft window includes a resistive probe penetrating an outer ply of the aircraft window, a first end of the probe being exposed at an outer surface of the outer ply of the aircraft window. A second end of the probe penetrates an inner surface of the outer ply of the aircraft window. A conductive drain element is disposed between the outer ply of the aircraft window and an inner ply of the aircraft window and is electrically connected between the second end of the probe and a ground point of the aircraft window. | 04-11-2013 |
| 20130119195 | MANUFACTURING METHOD FOR COMPOSITE MATERIAL STRUCTURAL COMPONENT FOR AIRCRAFT AND ITS STRUCTURAL COMPONENT - A method for manufacturing a structural component includes a first step of attaching at least one conductive member to a surface of a base material made of a composite material and a second step of forming the base material by conducting electricity to part or the whole of the conductive member to generate heat and/or making an assembly of the structural component by conducting electricity to part or the whole of the conductive member to generate heat. Part or the whole of the conductive member contained in the structural component produced in the first and second steps serves as a member giving to the aircraft at least one of a lightning strike protection function, an anti-icing and deicing function and an electromagnetic interference shielding function. | 05-16-2013 |
| 20130327888 | Conductive Coupling Assembly - A method and apparatus for conducting an electrical current between a first transport member and a second transport member. In one illustrative embodiment, a coupling assembly comprises a first fitting associated with a first end of a first transport member, a second fitting associated with a second end of a second transport member, and a seal. The seal is configured for placement around the first fitting and the second fitting when the first end of the first transport member is positioned relative to the second end of the second transport member. The seal is further configured to seal an interface between the first transport member and the second transport member. The seal is comprised of a material configured such that the seal has a level of conductivity within a selected range and such that a conductive pathway is formed between the first transport member and the second transport member. | 12-12-2013 |
| 20130341460 | FASTENER ASSEMBLY - A fastener assembly for attaching a component or bracket to the inner surface of the skin of an aircraft wing is disclosed. The fastener assembly comprises a bolt having a shaft and a bolt retaining member that threadingly cooperates with the shaft to retain the bolt in a position in which it extends through a hole in the skin. The fastener also includes a component or bracket retaining member that also threadingly cooperates with a portion of the shaft protruding through said bolt retaining member to attach a component or bracket to said inner surface. | 12-26-2013 |
| 20140021295 | LIGHTNING STRIKE PROTECTION - A lightning strike protection material may include a fiber reinforced composite aircraft component including carbon fibers in a resin matrix. The carbon fibers may have a length greater than at least about 6 mm and include carbon nanotubes grown on the fibers, and the nanotubes may be substantially uniformly distributed on the fibers and have a length between about 1 and 100 microns. The nanotubes may decrease a surface resistance of the resin matrix. | 01-23-2014 |
| 20140042270 | STORAGE SYSTEM FOR STORING STATIC ELECTRICAL ENERGY IN ATMOSPHERE - Embodiments of the invention relate to a system and method for collecting and storing static electrical energy in the atmosphere. An embodiment of the system comprises a control station, an airborne energy harvester with a fuselage, a collecting unit, and a storage module. The control station wireless communicates with the airborne energy harvester to control the movement of the airborne energy harvester. The collecting unit is mounted on a surface of the fuselage to collect the static electrical energy in the atmosphere. The storage module is located inside of the fuselage and includes at least one magnetic capacitor. The static electrical energy collected by the collecting unit is transferred and stored in the at least one magnetic capacitor. | 02-13-2014 |
| 20140091175 | Method and Apparatus for Covering a Fastener System - A method and apparatus for covering a fastener system. In one illustrative embodiment, an apparatus comprises a cover. The cover is configured to be placed over a fastener system at a surface of an object in which the fastener system is installed. The cover is comprised of a number of composite materials selected such that the cover is configured to reduce an effect of an electrical discharge, which occurs around the fastener system, on an environment outside the cover. | 04-03-2014 |
| 20140103160 | TIP FAIRING OF A HORIZONTAL AIRFOIL OF AN AIRCRAFT - A tip fairing of a horizontal airfoil of an aircraft is provided. The tip fairing comprises stiffening elements and a skin covering the stiffening elements. The stiffening elements comprise a central web and two flanges located at the tips of the web, with contact between the skin and the stiffening elements being made through the flanges of the stiffening elements. The tip fairing is manufactured from a composite material, is manufactured from a single part, and the planes defining the webs of any pair of stiffening elements taken in twos form an angle less than about 30°. | 04-17-2014 |
| 20140131513 | DOUBLE-CURVED COVER FOR COVERING A GAP BETWEEN TWO STRUCTURAL PORTIONS OF AN AIRCRAFT - A cover for covering a gap between a first structural portion and a second structural portion of an aerial vehicle. A first attachment section is attachable to the first structural portion. A second flexible section covers the gap. The second flexible section includes an abutment portion for abutting against the second structural portion in an operating state. The abutment portion in an unloaded state forms an undulating shape having troughs and crests extending along a curved plane. The curvature of the curved plane essentially corresponds with the curvature of the surface of the second structural portion. The troughs are provided for engagement with the surface in the operating state such that the troughs tend to be flatten out and propagate over the surface pressing down neighboring crests towards the surface for providing a close fit between the cover and the second structural portion. | 05-15-2014 |
| 20140158823 | HIGH ALTITUDE BALLOON SYSTEM - A high altitude balloon system includes a dual chamber balloon extending from an upper apex to a lower apex with a circumferential edge between the upper and lower apexes. A deflectable diaphragm is within the dual chamber balloon and coupled along the circumferential edge. The deflectable membrane divides the dual chamber balloon into a lift gas chamber formed by an interior surface of the dual chamber balloon and the deflectable diaphragm, and a ballast chamber formed by the interior surface of the dual chamber balloon and the deflectable diaphragm. Optionally, the dual chamber balloon is constructed by interposing the deflectable diaphragm between an upper and lower balloon panels. Each of the upper and lower balloon panels and the deflectable diaphragm are then coupled together along the circumferential edge to form both the lift gas chamber and the ballast chamber. | 06-12-2014 |
| 20140166805 | Lightning conductor system comprising a lightning conductor strip mounted in an offset manner - A lightning conductor system for a support structure having an external face intended to be subjected to a flow of air and an internal face opposite the external face, the lightning conductor system comprising an electrically conducting lightning conductor strip, intended to be placed on the side of the internal face of the support structure while being connected to ground, and means of fixing the lightning conductor strip to the support structure, the fixing means comprising fixing studs intended to be inserted into orifices formed in the support structure, said fixing studs being in electrical contact with the lightning conductor strip. The lightning conductor system includes the lightning conductor strip being mounted in an offset manner with respect to the main axes of the fixing studs. | 06-19-2014 |
| 20140197273 | Method for Producing a Surface Structure with Lightning Protection, and Surface Structure Which Can be Produced in This Way - A method for producing a surface structure with a lightning strike protective system involves providing a support structure based on a fiber-reinforced composite material. At least one arrangement of a lightning strike protective material made from or with a conductive material is applied onto the support structure so that the lightning strike protective material arrangement adheres to the support structure in such a way that it is held securely in its position. A cover material is applied in such a way that it embeds the at least one arrangement of a lightning strike protective material that is held securely in its position on the support structure, and the cover material is solidified. | 07-17-2014 |
| 20140209735 | ROTARY WING PLATFORM CONTAINMENT STRUCTURE FOR VERTICAL SURFACE TRANSFER - A method, device, and system for rotary wing aircraft for the purpose of rescuing trapped or injured people from vertical surfaces and structures, and transferring individuals or objects at vertical surfaces generally. The device consists of a containment structure, boom, counterweight, attachment point, and cockpit controls. The device is quickly attached to specially modified and equipped rotary wing aircraft, and placed in service to rescue people trapped in a high-rise building due to fire or other hazard and to rescue trapped or injured hikers and climbers from steep mountainous terrain or vertical rock surfaces. Applications include depositing personnel onto a vertical surface or the upper reaches of a vertical structure. | 07-31-2014 |
| 20140209736 | JIG FOR FORMING SEALANT LAYER FOR LIGHTNING PROTECTION FASTENER, METHOD FOR FORMING SEALANT LAYER FOR LIGHTNING PROTECTION FASTENER, AND WING OF AIRCRAFT - To provide a jig for forming a sealant layer which enables to quickly and accurately form a sealant layer having a required film thickness. The jig includes: a sealant cup | 07-31-2014 |
| 20140252164 | Aircraft with Electrically Conductive Nanocoating - A device has a first electrically conductive component, a second electrically conductive component, and an electrically conductive nanocoating (ECN) electrically connecting the first electrically conductive component to the second electrically conductive component. An aircraft has an engine, a fuselage, and a device having a first electrically conductive component, a second electrically conductive component, and an electrically conductive nanocoating (ECN) electrically connecting the first electrically conductive component to the second electrically conductive component. A method of providing an electrical conduction path includes providing a first electrically conductive component, providing a second electrically conductive component, and decreasing an electrical resistance between the first electrically conductive component and the second electrically conductive component using an electrically conductive nanocoating (ECN). | 09-11-2014 |
| 20140263830 | LAUNCH LIGHTNING RISK MITIGATION SYSTEM AND METHOD - A system and method for launching a launch vehicle in the presence of lightning. A processor detects potential sources of lightning and maneuvers one or more charge mitigation vehicles to locations proximate to the potential source of lightning such that at least one charge mitigation vehicle remains a better path to ground than the launch vehicle being launched at any given time during the launch. | 09-18-2014 |
| 20140374537 | Portable Airborne Multi-Mission Platform - A portable airborne multi-mission platform designed to collect meteorological data and perform other missions, either alone or in a modular array. Each portable airborne multi-mission platform comprises a tethered aerostat; a hydrogen generation, storage, and recovery system; and a control system. The tethered aerostat consists of an airship, a horizontal axis wind turbine, and a tether cable. The airship is both self-inflating and self-deflating and has the geometry of a wind concentrator and diffuser in fluid communication with the wind turbine. | 12-25-2014 |
| 20150090836 | Electromagnetic Energy Surface Protection - An electromagnetic energy protection system and method disclosed herein that includes a plurality of conductive sheets ohmically connected by conductive interconnects. The conductive interconnects can be metal formed by a metal deposition process. The metal deposition process can include a plasma deposition process. The conductive interconnects can help prevent the formation of surface deformities such as bumps that may be caused when connecting, either physically or electrically, adjacent conductive sheets. | 04-02-2015 |
| 20150102160 | LIGHTNING PROTECTION FASTENER AND AIRCRAFT - An aircraft of the present invention includes an outer panel | 04-16-2015 |
| 20150298819 | JIG FOR FORMING SEALANT LAYER FOR LIGHTNING PROTECTION FASTENER, METHOD FOR FORMING SEALANT LAYER FOR LIGHTNING PROTECTION FASTENER, LIGHTNING PROTECTION FASTENER, AND WING OF AIRCRAFT - To provide a jig for forming a sealant layer for a lightning protection fastener which enables to quickly and accurately obtain a sealant layer having a required thickness. A guide jig | 10-22-2015 |
| 20150298820 | APPARATUS FOR PREVENTING LIGHTNING STRIKE DAMAGE TO A STRUCTURAL COMPONENT - Preventing damage to a metal component or reducing manufacturing assembly steps. An initial channel, defined by an inner surface, is formed through the metal component. A bushing is placed into the initial channel, the bushing having an outer surface and an inner channel. An interference fit is created between the outer surface and the inner surface. A final channel is formed through the bushing. In forming the final channel, material is removed from the bushing to increase a size of the inner channel to be suitable to receive a fastener and such that the inner surface of the metal component remains unexposed within the final channel. The final channel extends through a second component. A fastener is placed into the final channel to attach the metal component to a second component, wherein electrical magnetic effects occur between the fastener and the bushing. | 10-22-2015 |
| 20150344151 | LIGHTNING-RESISTANT FASTENER, CAP, AND METHOD OF MOUNTING LIGHTNING-RESISTANT FASTENER - There are provided a lightning-resistant fastener and a cap, which, while assuring sufficient insulation properties, provide improved workability and highly stable quality to thereby enable a reduction in the manufacturing cost of an airframe, and a method of mounting the lightning-resistant fastener. A hole | 12-03-2015 |
| 20150367955 | FIRE-AND ELECTROMAGNETIC INTERFERENCE (EMI)-RESISTANT AIRCRAFT COMPONENTS AND METHODS FOR MANUFACTURING THE SAME - Fire- and electromagnetic interference (EMI)-resistant aircraft components and methods for manufacturing the same are provided. A thermally and electrically conductive coating material layer is formed on at least a portion of an intermediate article comprised of a non-metallic material. The thermally and electrically conductive coating material layer is comprised of a metal. A fire-retardant material layer is cold sprayed on the thermally and electrically conductive coating material layer. At least one continuous electrically conductive element may be integrated with the non-metallic material of the intermediate article. | 12-24-2015 |
| 20160009379 | One-Piece Composite Bifurcated Winglet | 01-14-2016 |
| 20160031569 | Lightning Protection Layer for Fiber Composite Structures - Specified is a lightning protection layer for an aircraft. The lightning protection layer has a first stratum and a second stratum. The second stratum is coupled to the first stratum along a connecting surface. The first stratum has a metal foil and the second stratum has carbon allotropes. It is thus made possible that damage to a structure of the aircraft by lightning strike is reduced. | 02-04-2016 |
| 20160052643 | LIGHTNING PROTECTION SYSTEM - A system comprising a low observable aircraft ( | 02-25-2016 |
| 20160083109 | METAL FASTENER - The invention relates to a metal fastener that makes it possible to ensure an electrically conductive surface along the entire thickness of structural elements to be assembled. The fastener thereby comprises a head and a smooth shank extending along an axis of revolution, characterized in that the shank comprises at least one conductive portion and one lubricating portion disposed along the axis of revolution of the fastener along at least one length of the shank. The inventive fastener makes it possible to ensure a conductive surface in the entire thickness of the structure in which it is installed. | 03-24-2016 |
| 20160130014 | METHOD FOR MANUFACTURING A PANEL MADE OF COMPOSITE MATERIAL INCORPORATING A LIGHTNING PROTECTION MEANS, AND PANEL MADE OF COMPOSITE MATERIAL MANUFACTURED BY WAY OF SAID METHOD - A method for manufacturing a panel made of composite material incorporating a lightning protection arrangement which comprises strips with a conductive layer. The method comprises a step of laying the strips in an automated manner, the strips having a width of less than 20 mm and being distributed in a first set of mutually parallel strips that are laid in a first laying direction and a second set of mutually parallel strips that are laid in a second laying direction that intersects the first laying direction. A panel made of composite material manufactured by way of this method is also disclosed. | 05-12-2016 |
| 20160137310 | METHOD FOR REPAIRING LIGHTNING PROTECTION MATERIAL, AND MEMBER PROVIDED WITH LIGHTNING PROTECTION MATERIAL - The present invention provides a method for repairing a lightning protection material that is made of a metal material and is provided along a surface of a member formed by using a fiber reinforced resin includes: bonding a repair material made of a metal material over a lost region of the member where the lightning protection material is lost by using a liquid adhesive and a sheet-shaped holder that contains and holds the adhesive and is arranged at the lost region. | 05-19-2016 |
| 20160144976 | STRUCTURAL ELEMENT - A structural element, in particular for an aircraft, such as an airplane, contains a laminate having a plurality of layers made of a fiber composite plastics material with carbon fibers, a lightning protection layer and optionally an electrically insulating dielectric protection layer. The laminate contains at least one hybrid layer, which comprises a carbon fiber-absorption fiber composite, the elongation at break of the absorption fiber being greater than the elongation at break of the carbon fibers. | 05-26-2016 |
| 20160169262 | METAL ATTACHMENT | 06-16-2016 |
| 20080237395 | BVI NOISE REDUCTION METHOD AND APPARATUS FOR HELICOPTER - The present method is characterized by providing the rotor blade with a tab | 10-02-2008 |
| 20080296431 | NOISE CONTROLLED TURBINE ENGINE WITH AIRCRAFT ENGINE ADAPTIVE NOISE CONTROL TUBES - An aircraft turbine engine with a takeoff fan speed and a landing fan speed, the aircraft engine includes a fan duct with a HQ (Herschel-Quincke) acoustic control noise reduction tube. The acoustic control noise reduction tube contains a movable frequency tuner obstruction. The movable frequency tuner obstruction is movable within the acoustic control noise reduction tube, with the movable frequency tuner obstruction movable along a fixed tube path length between a first takeoff frequency obstruction tube path location, and a second landing frequency obstruction tube path location, with the frequency tuner obstruction positioned at the first takeoff frequency location with the takeoff speed, and the frequency tuner obstruction positioned at the second landing frequency location with the landing speed to reduce noise. | 12-04-2008 |
| 20090078820 | WING-TO-BODY FAIRING - In one embodiment, a wing-to-body fairing for reducing noise due to wing-to-body fairing vibrations in at least one of an aircraft and a spacecraft comprises a honeycomb center comprising a cavity which is substantially filled with foam material. | 03-26-2009 |
| 20090078821 | LANDING GEAR - An aircraft noise-reduction apparatus ( | 03-26-2009 |
| 20090090812 | Insulation of an Aircraft Fuselage Structure - An insulating mat for the sound insulation of an aircraft fuselage structure that is composed of frames and stringers extending transverse to the frames, to a fastener means for fastening an insulating mat on an aircraft fuselage structure such that acoustic bridges are prevented. An insulating kit is also provided that comprises at least one insulating mat as well as at least one fastener. The insulating mat features a plurality of fastening clips that are fixed on a first surface of the insulating mat and laterally protrude over the border of the insulating mat. | 04-09-2009 |
| 20090152395 | ABSORBENT STRUCTURE FOR ATTENUATING NOISE PARTICULAR BY A ROTOR-GENERATOR NOISE, AND A ROTOR DUCT INCLUDING SUCH A STRUCTURE - An absorbent structure for reducing the propagation of soundwaves emitted by noisy devices such as rotors or motors, the structure includes a rigid partition ( | 06-18-2009 |
| 20090184200 | VIBRATION DAMPING FOR WING-TO-BODY AIRCRAFT FAIRING - A wing-to-body fairing for aircraft is formed from a sandwich structure having integrated vibration damping. | 07-23-2009 |
| 20090212158 | Aircraft Systems with Shape Memory Alloy (SMA) Actuators, and Associated Methods - Aircraft systems with shape memory alloy (SMA) actuators, and associated methods are disclosed. A system in accordance with one embodiment includes an airfoil, a deployable device coupled to the airfoil, and a shape memory alloy actuator coupled between the airfoil and the deployable device. In one embodiment, the deployable device can be coupled to the airfoil with a hinge having a hinge load path supporting the deployable device relative to the airfoil, and the actuator can be movable along a motion path different than the hinge load path between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil. In another embodiment, an activatable link can be positioned between the actuator and the deployable device, and can have an engaged configuration in which motion of the actuator is transmitted to the deployable device, and a disengaged configuration in which motion of the actuator is not transmitted to the deployable device. | 08-27-2009 |
| 20090256027 | Aerodynamic Noise Reducing Method (Variants) and Low-Noise Structural Element for Operating in a Fluid Medium Stream - The invention relates to aerodynamic. The inventive method for reducing the aerodynamic noise generated by separation a medium stream streaming around a structural element surface during the relative motion thereof consists in forming a low-curvature area consisting of at least one continuous section on at least one part of the structural element surface operating beyond the medium stream separation line and in orienting said structural element with respect to the medium stream in such a way that a normal line direction with a structural element surface is close to or coincides with the vector velocity direction of the medium stream on the entire or major part of the area surface. According to the second variant of the method the low-curvature is not formed at the production stage but is determined on the structural element surface of an existing structure using the features of the shape thereof. A low-noise structural element produced by the inventive method is also disclosed. The device also can be developed in such a way that it makes it possible to optimize the use thereof in particular application cases. The aim of the invention is to reduce the aerodynamic noise without deteriorating other aerodynamic characteristics of a structure. | 10-15-2009 |
| 20090283633 | INFILL PANEL OF A SUPPLY ARRANGEMENT IN A PASSENGER CABIN - A supply device in a passenger cabin, such as an aircraft passenger cabin, includes a first panel or “function panel” having one or more comfort elements, operating elements, visual display elements, and communication elements; and a second panel or an “infill panel”, which includes flexible supply channels. The panels are guided and lined up in a rail system of a PSC channel that is arranged in the direction of flight above a passenger seat row. The function panels are individually positionable in the PSC channel relative to the passenger seat row, wherein the infill panel synchronously follows a linear actuating movement of the function panel, and in this process automatically compensates for the distance dimension S | 11-19-2009 |
| 20090289146 | INTEGRATED ACOUSTIC DECOUPLING IN A HABITATION MODULE - According to an exemplary embodiment of the invention, a combined habitation module for the crew of an aircraft is provided, which habitation module comprises two monument units that are separated from each other by a gap such that acoustic decoupling of the two monument units from each other is provided. In this way noise propagation within the habitation module may be prevented to a large extent. | 11-26-2009 |
| 20090302154 | Material for absorbing noise in aircraft - The invention relates to a material for absorbing noise in aircraft, comprising at least one barrier layer and at least one absorptive layer. The barrier layer is provided with an elastomeric material having a minimum specific density of 1 and a mass per unit area of 1.3 kg/m | 12-10-2009 |
| 20090314885 | SYSTEM, METHOD AND APPARATUS FOR FLUIDIC EFFECTORS FOR ENHANCED FLUID FLOW MIXING - A fluidic effector provides enhanced plume mixing for an aircraft engine. Air jet injectors are located on both the external and internal cowl surfaces and angled in opposite directions to induce large scale vortices in the exhaust plume. The vortices mix actuation air with the exhaust plume to produce ejector action. The plume mixes out quickly, thereby lowering jet noise and jet exhaust temperature. The injectors have orientations and injection rates that are adjustable to allow variable mixing rates for use at different flight and engine conditions. | 12-24-2009 |
| 20090321559 | Aircraft noise reduction apparatus - The invention relates to aircraft noise reduction apparatus, in particular, but not exclusively, to noise reduction apparatus on an aircraft landing gear. The aircraft noise reduction apparatus comprises a noise reduction attachment for a landing gear of an aircraft. The noise reduction apparatus is movable between a first position in which it deflects air away from a noise inducing component of the landing gear and a second position in which it allows access to the noise inducing component. The movement of the noise reduction attachment between the first and second positions is actuated by a part of the landing gear. | 12-31-2009 |
| 20100006696 | Landing gear noise reduction assembly - An aircraft noise reduction apparatus including an aircraft landing gear assembly ( | 01-14-2010 |
| 20100006697 | LOW NOISE AIRCRAFT - A low noise aircraft which can reduce engine noise on the ground sharply at the time of take-off and landing by utilizing a well-known mechanism. By utilizing a thrust deflection means constituted of a well-known mechanism for making the direction of thrust variable, exhaust direction of an engine is deflected to the upper side (upward) of the course direction (flight direction) of the aircraft so that the maximum propagation direction of the engine jet exhaust noise is kept away from the ground, thus reducing the engine noise level on the ground at the time of aircraft take-off and landing. In particular, when the thrust deflection type exhaust nozzle ( | 01-14-2010 |
| 20100012777 | Supersonic Aircraft with Spike for Controlling and Reducing Sonic Boom - Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle. | 01-21-2010 |
| 20100012778 | Torque link set - An aircraft landing gear ( | 01-21-2010 |
| 20100038475 | ICE PROTECTION SYSTEM FOR A MULTI-SEGMENT AIRCRAFT COMPONENT - An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends. | 02-18-2010 |
| 20100038476 | DEVICE THAT MAKES IT POSSIBLE TO IMPROVE THE EFFECTIVENESS OF THE ACOUSTIC TREATMENTS IN A PIPE OF AN AIRCRAFT POWER PLANT - A device for improving the effectiveness of the acoustic treatment(s) in an aircraft propulsion unit that includes a pipe ( | 02-18-2010 |
| 20100044505 | HELICOPTER BLADE VORTEX INTERACTION NOISE REDUCING METHOD AND DEVICE - The present method is characterized by providing the rotor blade with a tab | 02-25-2010 |
| 20100065680 | DEVICE WITH PLANE JETS FOR REDUCING THE NOISE GENERATED BY A JET AIRCRAFT - The invention relates to an aircraft engine having a longitudinal axis (XX′), comprising a wall ( | 03-18-2010 |
| 20100084507 | REMOVABLE AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - The present invention relates to a nacelle ( | 04-08-2010 |
| 20100084508 | HIGH-LIFT DEVICE, WING, AND NOISE REDUCTION STRUCTURE FOR HIGH-LIFT DEVICE - The present invention provides high-lift devices, wings, and noise reduction structures for the high-lift devices capable of suppressing the occurrence of aerodynamic noise while restricting an increase in airframe weight. A high-lift device includes: a slat main body ( | 04-08-2010 |
| 20100108805 | Aircraft Landing Gear Provided With At Least One Noise Reducing Means - The invention relates to a landing gear including a noise reducing means ( | 05-06-2010 |
| 20100108806 | Hybrid propulsive engine including at least one independently rotatable propeller/fan - One aspect relates to a method of reducing noise for an aircraft. The method includes determining a mode of operation of the aircraft or the engine. The method also includes controlling a hybrid jet engine, based on the mode of operation, to at least partially use electrically generated torque to generate thrust. | 05-06-2010 |
| 20100108807 | TETHERED HOVERING PLATFORM - The design and refinement of a tethered hovering platform into a feasible working system is presented. To determine a starting point for the design, a detailed historical search was conducted to find the history and the current state of such technology. Real world current needs are analyzed to produce a mission specification and to drive the preliminary vehicle design. Analysis of environmental conditions and decisions about an initial payload package are made in conjunction with motor and propeller sizing. Initial concept testing to discover feasibility and operational issues was performed; from this, instability issues were discovered. Analyzing these instability issues using known rotorcraft and momentum effects, in conjunction with flight testing, yields possible solutions to the problem. The use of constrained layer dampers as a means of passive stabilization is addressed and suggested as the preferred solution. Testing of passive constrained layer damping verifies the stability of the solution. The system components and manufacturing cost is presented in comparison to current systems using active stabilization | 05-06-2010 |
| 20100133378 | ACOUSTIC PANEL HAVING A VARIABLE ACOUSTIC CHARACTERISTIC - An acoustic panel includes a reflective layer, at least one alveolar structure, and an acoustically resistive structure forming an aerodynamic surface of an aircraft on the surface of which at least one acoustic wave propagates along an axis of propagation ( | 06-03-2010 |
| 20100148001 | AIRCRAFT CABIN PANEL WITH CORE RECESSES FOR ACOUSTIC ABSORPTION - An aircraft cabin panel for acoustic absorption in an interior space includes a core layer, a first cover layer and a second cover layer. The first cover layer includes a space-enclosing first surface, and the second cover layer is arranged opposite the first cover layer. The first cover layer is acoustically transparent, and the core layer includes a honeycomb core with a plurality of tubular or honeycomb-like cells that are open throughout the thickness of the honeycomb core. The honeycomb core on the face pointing towards the first cover layer extends parallel to the first cover layer so as to be continuously throughout, and on the face pointing towards the second cover layer comprises recesses which extend over several cells. Absorbers are accommodated in the recesses. | 06-17-2010 |
| 20100155529 | Landing gear with noise reduction fairing - An aircraft noise reduction apparatus is provided which includes an aircraft landing gear assembly and a noise reduction fairing | 06-24-2010 |
| 20100170984 | ENGINE ASSEMBLY FOR AIRCRAFT WITH SLIDING NANCELLE - An aircraft engine assembly including a turbojet, a turbojet attachment pylon, and a nacelle mounted on the attachment pylon and surrounding the turbojet. The nacelle includes at least one mobile nacelle portion forming a single piece envelope all around a section of the turbojet, this mobile nacelle portion being mounted free to slide on the attachment pylon so that it can be moved from the forward position in the aft direction, and vice versa. | 07-08-2010 |
| 20100181420 | COATING FOR ACOUSTIC TREATMENT THAT INTEGRATES THE FUNCTION OF HOT-AIR TREATMENT OF FROST - The invention relates to a coating for acoustic treatment at the surface of an aircraft, in particular at the leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer ( | 07-22-2010 |
| 20100219288 | Deployable Flap Edge Fence - A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions. | 09-02-2010 |
| 20100252677 | AEROPLANE WITH IMPROVED ACOUSTIC COMFORT - An aircraft includes a cabin in which at least part of the space is demarcated by trim panels and the cabin is provided with a system for the active control of ambient noise. Each trim panel is either an active panel including actuators powered by the active noise control system or a passive panel without such actuators. In addition, the trim panels of the cabin of the one type, either active or passive, are mechanically interchangeable with a panel of the other type, either passive or active, respectively. Power supply wiring for active panels is installed in the aircraft, this wiring being capable of powering all active panels which could be installed, whether said active panels are actually installed or whether interchangeable passive panels are installed. Finally, a power supply system for the active panels is installed in the aircraft and connected to the power supply wiring of the active panels. | 10-07-2010 |
| 20100264264 | METHOD FOR PRODUCING AN AIRCRAFT WITH REDUCED ENVRIONMENTAL IMPACT AND THE AIRCRAFT THUS OBTAINED - A method for producing an aircraft with reduced environmental impact and the aircraft thus obtained. | 10-21-2010 |
| 20100282900 | System for Reducing Aerodynamic Noise at a Supplementary Wing of an Aircraft - A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which through an actuator device can be moved between at least one of the stable states and at least one additional state. | 11-11-2010 |
| 20100288876 | BLUFF BODY NOISE CONTROL - An aircraft noise-reduction apparatus comprise a flow-facing element ( | 11-18-2010 |
| 20100294882 | AIRCRAFT LEADING EDGE - An aircraft leading edge, such as, for example, an air intake ( | 11-25-2010 |
| 20100294883 | AERODYNAMIC SEAL FOR REDUCTION OF NOISE GENERATED ON AIRCRAFT CONTROL SURFACES - Flap side edge noise mechanisms have been addressed in a large number of studies during the last decades. A specific vortex system emanates from the flap side edge due to the static pressure difference between the upper and lower flap surfaces. Such pressure difference leads to a merging between the two vortex systems that are generated on the upper and lower edges of the flap side contour. The present invention intends to show the application of a perforated blade seal ( | 11-25-2010 |
| 20100301161 | ACOUSTIC COATING FOR AN AIRCRAFT INCORPORATING A FROST TREATMENT SYSTEM BY JOULE EFFECT - The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer ( | 12-02-2010 |
| 20100320316 | AIR INTAKE FOR AIRCRAFT NACELLE, AND PROPULSION ASSEMBLY INCLUDING SUCH AIR INTAKE - The invention relates to an air intake for an aircraft nacelle that comprises a shroud ( | 12-23-2010 |
| 20110001004 | Landing Gear - An aircraft landing gear is arranged such that in its deployed position it is configured to reduce, during the approach on landing, the noise generated by the interaction of the landing gear and the air flowing past the landing gear. Various means are described to reduce the amount of turbulent air flow generated in the region of the landing gear, including inverting and fairing the nose-gear shock-absorbing leg, providing faired twin in-line oleos and providing fairings that produce shielding air curtains. | 01-06-2011 |
| 20110068222 | PROPULSION UNIT FOR AN AIRCRAFT AND AIR INTAKE STRUCTURE FOR SUCH A UNIT - This propulsion unit for an aircraft comprises: a fan ( | 03-24-2011 |
| 20110079680 | Aircraft with tuned vibration absorber mounted on skin - An apparatus and method for attenuating noise and vibration in a propeller aircraft comprises a tuned vibration absorber adapted to be mounted to the skin of a fuselage of a propeller aircraft. The tuned vibration absorber may be tuned to the second harmonic of a blade passage frequency of a propeller of the aircraft. The tuned vibration absorber may be connectable to a separately formed mount, which can be mounted to the fuselage skin independently of the tuned vibration absorber. The apparatus may include a cover to prevent interference between the tuned vibration absorber and other components in the aircraft. The apparatus may be used in combination with other attenuation systems to attenuate noise and vibration over a broad range of frequencies. | 04-07-2011 |
| 20110089290 | AIRPLANE CONFIGURATION - An aircraft configuration that may reduce the level of noise, infrared radiation, or combination thereof directed towards the ground from an aircraft in flight. An embodiment of an aircraft includes a fuselage, two forward swept wings, at least one engine mounted to the aircraft and higher than the wings, and vertical stabilizers mounted on each wing outboard of the outermost engine. The leading edge of the wing may extend forward of the leading end of the engine, and the trailing edge of the aft deck may extend aft of the trailing end of the engine. The aft deck may include an upwardly rotatable pitch control surface at the trailing edge of the deck. Engine types may vary, including but not limited to turbofans, prop-fans, and turbo-props. Main wings may be mounted above the longitudinal axis of the fuselage, and canards may likewise be mounted above or below the axis. | 04-21-2011 |
| 20110114787 | ACOUSTIC TREATMENT PANEL WITH INTEGRAL CONNECTING REINFORCEMENT - An acoustic treatment panel includes, from the inside to the outside, a reflective layer ( | 05-19-2011 |
| 20110133025 | ACOUSTIC ATTENUATION PANEL FOR AIRCRAFT FOR ENGINE NACELLE - This acoustic attenuation panel for an aircraft engine nacelle comprises a structuring skin ( | 06-09-2011 |
| 20110139926 | Landing gear with noise reduction apparatus - An aircraft landing gear assembly comprises a landing gear ( | 06-16-2011 |
| 20110139927 | PANEL FOR AN AIR INTAKE OF AN AIRCRAFT NACELLE THAT ENSURES OPTIMIZED ACOUSTIC TREATMENT AND FROST TREATMENT - An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer ( | 06-16-2011 |
| 20110168839 | DEVICE FOR CONNECTING AN AIR INLET WITH AN AIRCRAFT NACELLE ACTUATOR ASSEMBLY - An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake. | 07-14-2011 |
| 20110180660 | AIRCRAFT HAVING A LAMBDA-BOX WING CONFIGURATION - Aircraft having a lambda-box wing configuration, comprising a fuselage ( | 07-28-2011 |
| 20110226897 | Launch vehicle fairing and construction - Light-weight acoustic dampening launch vehicle fairing structures having high strength and stiffness and capable of filling to provide high mass density and rapidly unloaded at a predetermined time following launch, and methods of making them are provided. The panels include a monolithic body comprised of fibrous reinforcement material in a polymeric binder and comprise longitudinal chambers extending from the length of body. Fluid passage means are provided at both the top and bottom of the monolithic body and interconnected by the longitudinal chambers for filling and emptying said chambers with a fluid. | 09-22-2011 |
| 20110248117 | MULTILAYER BOARD FOR ACOUSTIC INSULATION - A multilayer board is provided for acoustic insulation and to a method for producing said board. In order to reduce sound emission and at the same time improve stability, a multilayer board for acoustic insulation is proposed that includes, but is not limited to a core sheet, a first covering layer and a second covering layer. At least one of the two covering layers is of a closed design. The core sheet is arranged between the first covering layer and the second covering layer and is firmly connected in a planar fashion to the covering layers. Furthermore, the core sheet comprises slits that extend within the core sheet in the direction of the core sheet thickness, which slits reduce the shear stiffness of the board and thus ensure an improved acoustic insulation effect. On both sides the core sheet comprises continuous edge zones, which extend parallel to the covering layers, in order to, together with the covering layers, ensure the best possible stability of the board. The invention in particular also relates to an aircraft with an interior lining formed by panels that comprise the multilayer boards according to the invention in order to provide acoustic insulation. | 10-13-2011 |
| 20110284689 | AIRCRAFT CABIN PANEL FOR SOUND REDUCTION - The present invention relates to an aircraft cabin panel for sound reduction in an interior space. The invention in particular also relates to an aircraft comprising an interior lining with sound-absorbing and sound-reducing panels. In order to provide a panel that is optimized in terms of the design space required by it and in terms of its weight, for use in aircraft, which panel provides improved sound reduction and sound absorption characteristics, an aircraft cabin panel for sound reduction in an interior space is provided, which aircraft cabin panel in at least one region comprises a sandwich construction with a core layer, a first covering layer and a second covering layer. The core layer comprises sound absorbing open-pore core material. The first and the second covering layer are connected to the core layer in a planar fashion. The first covering layer is arranged towards the sound waves to be absorbed and the second covering layer is arranged opposite the first covering layer. The first covering layer is designed so as to be acoustically transparent. | 11-24-2011 |
| 20110303786 | SILENCER FOR AN AUXILIARY POWER UNIT OF AN AIRCRAFT - A silencer for an auxiliary power unit of an aircraft comprises an inlet, an outlet, a housing and a flow channel with a porous wall material that is arranged in the housing. An intermediate space is formed between the housing and the flow channel and divided into outer cells that are arranged around the flow channel by means of one or more partitions. This makes it possible to realize a very compact silencer with very good sound insulation properties. The sound dampening can be additionally improved by dividing the outer cells into outer regions and inner regions, by adapting the shape of the silencer to a tail section of an aircraft and by arranging an annular channel on the outlet. | 12-15-2011 |
| 20110315819 | Supersonic Aircraft with Spike for Controlling and Reducing Sonic Boom - Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region there between and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle. | 12-29-2011 |
| 20120001022 | JET ENGINE INSTALLATION - Noise generated by a gas turbine engine | 01-05-2012 |
| 20120012698 | AIRCRAFT COMPRISING AN INSULATION SYSTEM FOR THERMAL AND ACOUSTIC INSULATION - The invention relates to an aircraft comprising an insulation system for thermal and acoustic insulation. Said insulation system includes a cabin, an outer skin, a sound insulating unit, and a heat insulating unit. The sound insulating unit is designed to acoustically insulate the aircraft. The heat insulating unit is designed to thermally insulate the aircraft. The sound insulating unit and the heat insulating unit are arranged between the cabin and the outer skin. | 01-19-2012 |
| 20120025016 | AIRCRAFT PROPELLER - A propeller for an aircraft is disclosed. The propeller has an odd number of unequally circumferentially spaced blades. The propeller may be provided as part of a contra-rotating propeller arrangement and/or aft of a pylon on an aircraft. The propeller has been found to reduce noise levels and to be efficient. | 02-02-2012 |
| 20120032024 | WING-TO-BODY FAIRING WITH SPRAY-ON FOAM AND NOISE REDUCTION METHOD - A fairing includes a fairing body having a fairing interior and an interior surface and a spray-on insulation foam layer provided on the interior surface of the fairing body. | 02-09-2012 |
| 20120068011 | Active Aircraft Pylon Noise Control System - An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure. | 03-22-2012 |
| 20120068012 | ARRANGEMENT AND AIRCRAFT OR SPACECRAFT - The present invention provides an arrangement, in particular for an aircraft or spacecraft, comprising an outer skin portion, the outside of which comes into contact with the atmosphere; a facing portion, which is arranged on the inside of the outer skin portion; a gap which is formed between the outer skin portion and the facing portion; and a device by means of which an airstream can be passed through the gap at a sufficient temperature to displace the dew point into the outer skin portion. | 03-22-2012 |
| 20120085861 | DEVICE FOR ACOUSTIC TREATMENT OF THE NOISE EMITTED BY A TURBOJET - The invention provides a device for acoustical treatment of the noise emitted by a bypass turbojet comprising a primary cowl having in an outer surface an inner annular acoustic treatment panel and a secondary cowl including in an inner surface an outer annular acoustic treatment panel arranged facing the inner panel. The inner and outer panels include respective central panel portions facing each other and extending axially over a common predetermined length, the length of the central panel portions lying in the range one-fifth to four-fifths of the total length of the panels, and the ratio between the acoustic resistances of the central panel portions being not less than 2. | 04-12-2012 |
| 20120091270 | AIRCRAFT CONFIGURATION - An aircraft configuration that may reduce the level of roaring jet exhaust noise, infrared radiation, sonic boom, or combination thereof directed towards the ground from an aircraft in flight. The aircraft's nacelles are mounted to the aircraft higher than the wings, with substantially vertical stabilizers outboard of the outermost engine. Noise shifting means are provided such as, for each nacelle, primary chevrons at the core nozzle, secondary chevrons at the fan nozzle, a partial bypass mixer, a long duct full flow mixer, or a combination thereof to provide a shift in spectrum distribution of jet exhaust noise from lower to higher frequency. Variable geometry chevrons may be used with increased immersion to provide such a shift just during noise-restricted portions of an aircraft flight profile. The aircraft aerodynamic structural surfaces serve as noise shielding barriers that more effectively block or redirect the frequency shifted noise up and away from communities. | 04-19-2012 |
| 20120097791 | Autonomous Slat-Cove-Filler Device for Reduction of Aeroacoustic Noise Associated with Aircraft Systems - A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction. | 04-26-2012 |
| 20120119023 | METHOD AND APPARATUS FOR REDUCING AIRCRAFT NOISE - An arrangement for an aircraft includes a fuselage, a wing, and a propulsor. The wing may have a wing upper surface, a rear spar and a wing trailing edge. The propulsor may include at least one rotor having a rotor diameter and a rotor axis. The propulsor may be mounted such that the rotor is located longitudinally between the rear spar and the wing trailing edge. The propulsor may also be mounted such that a lowest point of the rotor diameter is located vertically above the wing upper surface. | 05-17-2012 |
| 20120119024 | INSULATION ARRANGEMENT IN AN AIRCRAFT - An insulation arrangement with a holding device that comprises a collar forms an overlapping region between a second insulating package and the collar such that incidental condensation water on a first insulation package drains to the second insulating package along the collar under the influence of the gravitational force and from there into a bilge of the aircraft equipped with the insulation arrangement on a waterproof cover film of the second insulating package. This prevents condensation water from dripping into a passenger cabin. | 05-17-2012 |
| 20120145826 | HIGH-LIFT-DEVICE, WING, AND NOISE REDUCTION DEVICE FOR HIGH-LIFT-DEVICE - In a high-lift-device, a wing, and noise reduction device for a high-lift-device that are capable of reducing noise generated when a flap is extended, preventing deterioration of aerodynamics characteristic when retracting the flap, and preventing an increase in weight, a flap main body ( | 06-14-2012 |
| 20120211599 | FLOW-MODIFYING FORMATION FOR AIRCRAFT WING - An aircraft wing has an engine attachment position at which a gas turbine engine is attached beneath the wing, in use the engine ejecting a propulsive gas jet with a jet shear layer being formed between the gas jet and the surrounding air. The aircraft wing further has one or more elongate, flow-modifying formations protruding from the underside of the wing. The length direction of the or each formation is along the fore and aft direction of the wing with the trailing edge of the formation being rearward of the trailing edge of the wing. The flow-modifying formations can be arranged such that they interact with the jet shear layer to reduce noise generated by the interaction of the jet shear layer and the wing. They can also be arranged to block, attenuate and/or to scatter the noise reflected by the wing. | 08-23-2012 |
| 20120256048 | Vibration Isolation System - A vibration isolation system for attenuating vibration energy between two aircraft structures, such as between the aircraft's fuselage and interior cabin. The vibration isolation system includes a first isolator attached to the first structure, a second isolator attached to the second structure, and an intermediate mass attached between the first and second isolators. The intermediate mass may be electrical cables, wiring bundles, a cable holder, or other component disposed between the two structures. Cable holder intermediate masses can be fabricated from an electrically conductive material to provide electromagnetic interference shielding for cables disposed therein. Multiple vibration isolation systems can be disposed between the fuselage and interior cabin to provide a less noisy cabin. Additional noise and vibration suppressors, such as skin damping material and acoustic blankets, also can be disposed between the fuselage and interior cabin to further reduce noise in the interior cabin. | 10-11-2012 |
| 20120256049 | Systems and Methods for Attenuation of Noise and Wakes Produced by Aircraft - Systems and methods for reducing the trailing vortices and lowering the noise produced by the side edges of aircraft flight control surfaces, tips of wings and winglets, and tips of rotor blades. A noise-reducing, wake-alleviating device is disclosed which incorporates an actuator and one or more air-ejecting slot-shaped openings coupled to that actuator and located on the upper and/or lower surfaces and/or the side edges of an aircraft flight control surface or the tip of a wing, winglet or blade. The actuation mechanism produces sets of small and fast-moving air jets that traverse the openings in the general streamwise direction. The actuation destabilizes the flap vortex structure, resulting in reduced intensity of trailing vortices and lower airplane noise. | 10-11-2012 |
| 20120267475 | ACOUSTIC SEAL FOR AIRCRAFT - An acoustic seal device is placed around the periphery of aircraft doors for reducing reducing wind noises transmitted into the aircraft cabin by the door gaps without adding additional weight to the aircraft. The acoustic seal includes a pre-shaped body made of a soundproofing material. The pre-shaped body is adapted to be secured to a door opening and has a shape that matches the shape of the door opening. | 10-25-2012 |
| 20120267476 | ACOUSTICALLY OPTIMIZED AIR CONDITIONING COMPONENTS - Systems and methods for sound damping in air conditioning systems in an aircraft is provided. In one embodiment, an air conditioning conduit can comprise a sound-damping wall that at least partially encloses a continuous hollow space for guiding the air. The wall comprises a multilayer design with a core layer and at least one first cover layer. The core layer comprises a sound-absorbing open-pore core material so that the wall shows an acoustic effect. The first cover layer is airtight, is arranged on the external surface of the core layer, and is two-dimensionally connected to the core layer. The two-dimensional connection between the core layer and the first cover layer causes a composite effect in such a manner that the wall is self-supporting and has a structural function in order to be able to transfer mechanically-occurring loads to structural parts of the aircraft. | 10-25-2012 |
| 20120273611 | EXHAUST SILENCER WITH BAFFLES - An exhaust silencer assembly includes an exhaust duct and an exhaust silencer. The exhaust silencer is disposed about the exhaust duct and has a plurality of solid baffles and at least one perforated baffle The exhaust silencer assembly is disposed downstream of an auxiliary power unit and at least partially attenuates the downstream noise of the combustion gases that result from operation of the auxiliary power unit. In one embodiment, at least one of the plurality of solid baffles is disposed to extend axially between generally radially extending solid baffles, perforated baffle(s), or partially perforated baffles. The axially extending solid baffle allows for cavity depth variation in the silencer to optimize tuning of particular frequencies from the auxiliary power unit. | 11-01-2012 |
| 20120292440 | Mass flow increase at takeoff in supersonic airliner - In a supersonic aircraft, turbojet engine nacelles each containing two remote fans in the front half of the nacelle, for noise reduction at takeoff. During supersonic flight, a front wedge at the nacelle nose achieves external compression of intake air. The wedge is vertical, sending the airflow left and right inside the nacelle along its side walls. The two flows follow mirror image curved paths on their way to a turbojet, leaving unused space between them to house the fans in tandem. For takeoff, clutches connected to the turbojets's compressors are engaged. Driveshafts turn pinions against a gear on the same shaft as the remote fans. The fan output is discharged backward under the nacelle to produce thrust. The energy to turn the fans is taken from the turbojet cycle. The reduced exhaust jet velocity decreases its noise. Supercharging produces the extra power to turn the remote fans if multistage. | 11-22-2012 |
| 20120292441 | SYSTEM AND METHOD FOR REDUCING THE NOISE OF PUSHER TYPE AIRCRAFT PROPELLERS - A system and method for reducing the noise penalty of a pusher propeller, allowing an aircraft to retain its advantages for UAV configurations, while allowing acoustic performance similar to that of a tractor propeller by reducing, or eliminating, propeller noise emissions. The system and method provide an airfoil-shaped flight surface with (i) a scoop configured to route boundary layer air and associated wake from said flight surface, and (ii) a suction device configured to provide a suction pressure, wherein the scoop routes boundary layer air from the flight surface to the suction device via an opening in the flight surface. | 11-22-2012 |
| 20130009002 | TURBOSHAFT ENGINE SUPPORTING PYLON COVERED WITH A POROUS MATERIAL AND TURBOSHAFT ENGINE/PYLON ASSEMBLY - A turboshaft engine supporting pylon covered with a porous material and a turboshaft engine/pylon assembly. The pylon supports a turboshaft engine on an aircraft, and includes an outer surface covered at least partially with a porous material to reduce amplitude of acoustic waves leaving the turboshaft engine. The assembly includes a turboshaft engine and a pylon, in which the pylon extends longitudinally from upstream to downstream and includes an upper part for securing to the aircraft, a lower part for securing to the turboshaft engine, and an absorption part extending in an exhaust stream from the turboshaft engine and including an internal absorption part extending inside the turboshaft engine and an external absorption part extending downstream of the turboshaft engine. The outer surface of the upstream end of the external absorption part of the pylon is covered with a porous material to limit noise formation downstream of the engine. | 01-10-2013 |
| 20130020434 | Condensed Water Decreasing Insulation Package For Thermal And Acoustic Insulation Of A Vehicle Cabin - An insulation package for thermal and acoustic insulation of a vehicle cabin has a cutout to allow a fastening device to pass through. An insulating element that is disposed in an area of the insulation package surrounding the cutout has an opening corresponding to the cutout for allowing a fastening device to pass through. At least part of the insulating element is aligned perpendicularly to an axis of the passthrough in the cutout and conformed so as to create a gap between a fastening device that has passed through and the insulation package. In this way, condensed water may be prevented from passing through the cutout in the insulation package and into the aircraft cabin. | 01-24-2013 |
| 20130026288 | Aircraft Comprising At Least One Net For Reducing Aerodynamic Noise From A Structural Element Of Said Aircraft - The invention relates to an aircraft comprising at least one net for reducing aerodynamic noise from a structural element of said aircraft. According to the invention, the flexible net ( | 01-31-2013 |
| 20130032664 | COUNTER-TORQUE DEVICE FOR A HELICOPTER - A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub. | 02-07-2013 |
| 20130043343 | METHOD OF PROCESSING ACOUSTIC WAVES EMITTED AT THE OUTLET OF A TURBO ENGINE OF AN AIRCRAFT WITH A DIELECTRIC-BARRIER DISCHARGE DEVICE AND AIRCRAFT COMPRISING SUCH A DEVICE - A method of processing acoustic waves emitted at an outlet of a turbo engine of an aircraft with a dielectric barrier discharge device, and an aircraft including such a device. The method includes activating the dielectric barrier discharge device so as to emit an electric wind in a direction of acoustic waves so as to attenuate the acoustic waves. An aircraft can include such a dielectric barrier discharge device. | 02-21-2013 |
| 20130056581 | Rijke Tube Cancellation Device for Helicopters - An acoustic signature reduction system for application typically on an aircraft. The acoustic signature reduction system uses a controller, power supply, and a thermo-acoustic tube such as a Rijke tube or Sondhauss tube to generate a cancellation noise of equal amplitude and inverted to that of noise generated by rotor blades when rotating. Acoustic signature reduction system can use a damping valve to make an intermittent cancellation sound to match the n/rev signature of the rotor blades with respect to a given reference location. The n/rev timing is different depending on the reference location therefore a cone of silence is created. A forced air unit may also be used to modify the phase of the cancellation noise in order to move the cone of silence around the aircraft. | 03-07-2013 |
| 20130175392 | QUIET LANDING ATTITUDE MODIFIER FOR AIRPLANE - The present invention provides a method of modifying the pitch attitude of an aircraft during landing, comprising: commanding the flaps to move to a landing setting; providing a current value for a flight condition parameter; providing a current flaps setting; comparing said current value to at least one threshold value; if said current value exceeds said threshold, determining a new flaps setting capable of producing an improvement in at least one of a selected aft body contact margin and a selected nose gear contact margin for the aircraft; and adjusting the flaps to said new flaps setting. | 07-11-2013 |
| 20130193268 | BLUFF BODY NOISE CONTROL - An aircraft noise-reduction apparatus comprise a flow-facing element ( | 08-01-2013 |
| 20130240668 | CONDENSATION WATER-FREE INSULATION SYSTEM FOR PASSENGER AIRCRAFT - An insulation arrangement for thermally and acoustically insulating an aircraft fuselage, which comprises at least one insulation packet arranged on an exterior skin of the aircraft. The insulation packet includes dimensionally rigid foam, and comprises a shape corresponding at least with a structural component on the exterior skin, as the result of which the insulation packet is retained on the structural component even without any additional attachment elements. As a result, ventilation openings need not be provided, thereby reducing condensation water accumulating in aircraft insulation. | 09-19-2013 |
| 20130248649 | ACOUSTICALLY AND THERMALLY INSULATED GALLEY SHELL - The present invention is a light weight, easily fitted, and removable protective panel for an aircraft galley monument that incorporates a thermal barrier for heat loss control. The thermal barrier encloses a high percentage of the cold bridges between the chilled compartments of a galley cooler and the ambient surroundings, allowing an aircraft galley cooler to efficiently and economically meet its target temperature. The protective panel is multi-configurable and capable of being customized to the requirements of a particular aircraft. | 09-26-2013 |
| 20130299630 | INSULATION ARRANGEMENT WITH VENTILATION OPENINGS FOR AIRCRAFT - An insulation arrangement with two or more insulation packages that overlap such that at least one overlapping region is formed and are arrangeable on a fuselage wall is provided. The insulation packages comprise an insulating material and welded cover films. The cover films are realized in an airtight and waterproof fashion and comprise ventilation openings on a side that is directed toward the fuselage wall in an overlapping region. In this way, pressure variations in the insulation packages can be compensated with relatively dry air that originates from a gap between the insulation packages and the fuselage wall in order to thusly reduce the accumulation of condensation water in the insulation packages. | 11-14-2013 |
| 20130334365 | AIRCRAFT WITH REDUCED ENVIRONMENTAL IMPACT - An aircraft with reduced environmental impact includes two turboprop engines mounted on the back of the aircraft at the rear thereof, and one acoustic masking device per turboprop engine. The acoustic masking device includes a masking element, such as a flap, which can move between a position in which it is retracted into the wing, and a position in which it is extended toward the rear of the wing. In the extended position, the flap intercepts the noise area generated toward the front by the turboprop engine, so as to reduce the perception of noise on the ground. | 12-19-2013 |
| 20140027569 | WING-TO-BODY FARING WITH SPRAY-ON FOAM AND NOISE REDUCTION METHOD - A fairing includes a fairing body having a fairing interior and an interior surface and a spray-on insulation foam layer provided on the interior surface of the fairing body. | 01-30-2014 |
| 20140070051 | EMPENNAGE OF A HELICOPTER - An empennage ( | 03-13-2014 |
| 20140077031 | METALLIC SANDWICH STRUCTURE HAVING SMALL BEND RADIUS - An acoustic-attenuating wall panel for a nacelle of a turbine engine may include a radiused portion. The radiused portion may include an airflow surface having a concave configuration and which may be exposed to an airflow passing through the nacelle. The radiused portion may include an acoustic attenuating section. | 03-20-2014 |
| 20140151498 | QUIET LANDING GEAR DOOR - A quiet landing gear door and methods are presented. A landing gear door comprises a trailing edge and a leading edge and is operable to deploy to a landing gear door deployed position. A door flap comprises the trailing edge and is hinged to the landing gear door. The door flap deflects toward a landing gear strut to a door flap deployed position in response to deployment of the landing gear door. A leading edge section comprises the leading edge and is coupled to the door flap. The leading edge section deflects toward the landing gear strut to a leading edge deployed position in response to deployment of the landing gear door. | 06-05-2014 |
| 20140209737 | WING FLAPS FOR AIRCRAFT AND METHODS FOR MAKING THE SAME - Flaps for operatively coupling to wing main elements of aircraft, aircraft including such flaps and methods for making such flaps are provided herein. In one example, a flap for operatively coupling to a wing main element of an aircraft comprises an outer flap section that has a side edge portion. The side edge portion at least partially surrounds a flap side-edge cavity. A porous cavity-filler insert is positioned in the flap side-edge cavity. | 07-31-2014 |
| 20140217236 | VARIABLE-WIDTH AERODYNAMIC DEVICE - There is described a variable-width aerodynamic device ( | 08-07-2014 |
| 20140246541 | METHOD FOR THE GUIDANCE OF A ROTORCRAFT, WHICH METHOD LIMITS NOISE DISCOMFORT IN A PROCEDURE FOR THE APPROACH TO A LANDING POINT - A method for the guidance of a rotorcraft ( | 09-04-2014 |
| 20140263831 | Cross-wing Twin-Fuselage Aircraft - A dimensionally size-efficient aircraft being of a twin-fuselage configuration that addresses long-range high-capacity passenger commercial or military application needs, unique in that propelling engines (two, three, or four engine arrangements) are centrally mounted aft of a central cross-wing section, that section addressing the structural requirements of fuselage attachment with a means of passage between fuselages, the outer main wings being free from hanging appendages, thereby enabling efficient aerodynamic-lift wing design, the configuration using a split stabilizer and a split vertical tail for stable aerodynamic control. Engine locations are biased high and aft with the central and outer wings providing ground noise abatement while in flight, passenger cabin noise low due to aft engine locations. | 09-18-2014 |
| 20140299710 | HOVER-CAPABLE AIRCRAFT - A hover-capable aircraft having propulsion means; at least one rotor; transmission means for transmitting power from the propulsion means to the rotor and lubricated with a lubricant; a heat exchanger, which receives the heated lubricant from the transmission means and feeds the cooled lubricant back to the transmission means; and a fan for producing airflow through the heat exchanger to cool the lubricant, and which has an impeller with blades, and an exhaust pipe for expelling the hot air produced by cooling the lubricant; at least one portion of the wall of the exhaust pipe has dissipating means designed to selectively absorb pressure waves in a given frequency band related to the rotation speed of the impeller and to the number of blades of the impeller. | 10-09-2014 |
| 20140306058 | Supersonic Aircraft with Spike for Controlling and Reducing Sonic Boom - Method and arrangement for reducing the effects of a some boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region there between and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle. | 10-16-2014 |
| 20140367512 | HONEYCOMB CORES WITH SPLICE JOINTS AND METHODS OF ASSEMBLING HONEYCOMB CORES - Honeycomb cores for use in aerospace applications include two honeycomb core sections operably joined at a splice joint, the splice joint defined by a foam adhesive that is sandwiched between a sheet of film adhesive. Methods of assembling honeycomb cores also are disclosed herein. | 12-18-2014 |
| 20150008281 | AIRCRAFT INTERIOR TRIM PANEL, AND AIRCRAFT FITTED WITH SUCH PANELS - A trim panel for the interior of an aircraft, the panel having a multilayer structure and including an outer layer made of material impervious to air, and which is positioned in use facing the fuselage of the aircraft; an inner layer made of trim material, and which in use defines the interior; a structural layer interposed between the inner and outer layer; and acoustic energy dissipating material, also interposed between the inner and outer layer; the inner layer being made of porous material allowing airflow towards the acoustic energy dissipating material. | 01-08-2015 |
| 20150053816 | AIRCRAFT LANDING GEAR - An aircraft landing gear which includes a noise-inducing region and a cover. The cover comprises a cover portion arranged to enclose the noise-inducing region to inhibit an airflow negotiating the noise-inducing region when the landing gear is in use. | 02-26-2015 |
| 20150083855 | LEADING EDGE SYSTEM AND METHOD FOR APPROACH NOISE REDUCTION - A slat control system for an aircraft may include a flight control computer configured to generate a gap command in response to an occurrence of a gap-command condition. The slat control system may further include an edge control system including an edge control device having a plurality of control device positions including at least one designated control device position. The slat control system may additionally include a device actuation system configured to move a leading edge device of an aircraft. The edge control system may be configured to automatically command the device actuation system to extend the leading edge device from a sealed position to a gapped position when the edge control device is in the designated control device position and the gap command is received by the edge control system. | 03-26-2015 |
| 20150102161 | METHOD FOR A LEADING EDGE SLAT ON A WING OF AN AIRCRAFT - A method for managing a flight control surface system. A leading edge device is moved on a leading edge from an undeployed position to a deployed position. The leading edge device has an outer surface, an inner surface, and a deformable fairing attached to the leading edge device such that the deformable fairing covers at least a portion of the inner surface. The deformable fairing changes from a deformed shape to an original shape when the leading edge device is moved to the deployed position. The leading edge device is then moved from the deployed position to the undeployed position, wherein the deformable fairing changes from the original shape to the deformed shape. | 04-16-2015 |
| 20150102162 | QUIET LANDING GEAR DOOR - A quiet landing gear door and methods are presented. A landing gear door comprises a trailing edge and a leading edge and is operable to deploy to a landing gear door deployed position. A door flap comprises the trailing edge and is hinged to the landing gear door. The door flap deflects toward a landing gear strut to a door flap deployed position in response to deployment of the landing gear door. A leading edge section comprises the leading edge and is coupled to the door flap. The leading edge section deflects toward the landing gear strut to a leading edge deployed position in response to deployment of the landing gear door. | 04-16-2015 |
| 20150144734 | AIRCRAFT INTERIOR PANEL WITH ACOUSTIC MATERIALS - A panel assembly that includes a first panel having an inner surface and an outer surface, and a second panel having an inner surface and an outer surface. The second panel includes a plurality of rib members formed therein that extend inwardly. The rib members include an inner surface and an outer surface. A plurality of panel portions are defined between the plurality of rib members. The panel portions include an inner surface and an outer surface. The inner surface of the rib members are secured to the inner surface of the first panel, and the inner surface of the panel portions is spaced apart from the inner surface of the first panel to define at least first and second cavities. | 05-28-2015 |
| 20150375848 | AIRCRAFT AIR SCOOP SYSTEMS WITH PASSIVE PNEUMATIC ACTUATORS - Aircraft and air scoop systems are provided. An aircraft includes an interior compartment, an outer skin, an air scoop, it movable element, and a passive pneumatic actuator. The interior compartment encloses a substantially constant interior air mass at a cabin pressure during flight and the outer skin at least partially defines a ventilated cavity. The air scoop is disposed on the outer skin and communicates air between the ventilated cavity and an external environment in which the aircraft is located. The movable element is movable between an open position and a closed position over the air scoop to define an air flow area through the air scoop. The passive pneumatic actuator is operatively coupled with the movable element and moves the movable element towards the closed position in response to an increasing altitude of the aircraft based on a differential pressure between the interior air mass and the external environment. | 12-31-2015 |
| 20160101845 | AIRCRAFT AND AIR EXCHANGE SYSTEMS FOR VENTILATED CAVITIES OF AIRCRAFT - Aircraft, wing-to-body fairing assemblies, and air exchange systems are provided. An aircraft includes a fuselage, a wing secured to the fuselage, an outer skin panel, and an air exchange system. The outer skin panel is secured to the wing and/or the fuselage and at least partially defines a cavity. The air exchange system is secured to the outer skin panel and exchanges air between the cavity and an external environment. The air exchange system includes an air inlet, a diffuser, and a silencer. The air inlet is disposed in the outer skin panel and accommodates an air flow between the cavity and the external environment. The diffuser is attached to the air inlet and has a varying cross sectional area to change the speed of the air flow. The silencer is attached to the diffuser and communicates the air flow between the diffuser and the cavity and reduces noise. | 04-14-2016 |
| 20160137284 | AUTONOMOUS SLAT-COVE-FILLER DEVICE FOR REDUCTION OF AEROACOUSTIC NOISE ASSOCIATED WITH AIRCRAFT SYSTEMS - A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction. | 05-19-2016 |
| 20160375990 | Landing Gear Noise Abatement Devices - A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag. | 12-29-2016 |
| 20180022445 | LANDING GEAR NOISE ABATEMENT DEVICES | 01-25-2018 |
| 20080217474 | Method and apparatus for fast deploying and retrieving of towed bodies - In a method and apparatus for controlling the deployment of a towline connecting a mooring craft to an ejected object comprising the steps of monitoring velocity to determine when a point for optimum braking has been achieved and then engaging a brake system to retard deployment of the towline, a DC motor augments and controls the brake system. The DC motor further controls the retrieval of the object. A cutter mechanism uses a first blade to grip the towing cable to maintain tension thereon as a second blade cuts the cable. A spring biased boom in combination with spring biased fins on the ejected object rapidly deploys the object from its storage housing. A locking mechanism secures the deployment mechanism in a stable locked position upon the object reaching its fully extended position. | 09-11-2008 |
| 20090065639 | Separate Communication Line for Towed Body - The present invention relates to a system for connecting an aircraft to a towed body, which comprises: (a) a reduced towing cable comprising tension filaments to provide the tensional force required for towing the body; (b) a signal cable, separate from said reduced towing cable, for conveying signals between the aircraft and the towed body, said signal cable comprises one or more optical fibers; and (c) conductive wires either within said towing cable or within said signal cable for providing electrical path between the aircraft and the towed body. | 03-12-2009 |
| 20090127387 | Method for recovering a relatively slower moving vehicle - A method whereby a relatively faster-moving vessel recovers a relatively-slower moving vehicle is disclosed. | 05-21-2009 |
| 20090206198 | AIRCRAFT ENGINE STRUCTURE-MOUNTED AIM-POINT BIASING INFRARED COUNTERMEASURE APPARATUS AND METHOD - A thermal radiation-generating decoy mounted adjacent an aircraft engine structure, such as an engine nacelle, includes a heat source inside of an aerodynamic enclosure with a mounting interface to attach the enclosure to the engine structure. The decoy can further be located at the lower extreme of and adjacent the forward-most portion of the engine nacelle in order to attract an infrared-seeking threat to the vicinity of the fan containment portion of the engine nacelle. The decoy can be designed to have a thermal signature that mimics a scaled overall aircraft thermal signature. In addition, the decoy can include a fuse shield adjacent the enclosure to detonate a threat in the case that the threat approach trajectory is imprecise and the threat bypasses the enclosure within an aspect of the fuse shield as viewed from the approach direction of the threat. | 08-20-2009 |
| 20090314886 | DEPLOYMENT OF TELESCOPING AIRCRAFT STRUCTURES BY DROGUE PARACHUTE RISER TENSION - A system for deploying a deployable structure in an aircraft, comprising a drogue parachute, at least one deployable structure, a riser line attached to the drogue parachute and the at least one deployable structure, wherein when the drogue parachute is deployed, a tension is applied to the riser line, and a parachute deployment system, wherein the parachute deployment system is configured to utilize the applied tension to deploy the at least one deployable structure. | 12-24-2009 |
| 20100038477 | SYSTEM AND METHODS FOR AIRBORNE LAUNCH AND RECOVERY OF AIRCRAFT - A system and methods for airborne launch and recovery of aircraft. In one embodiment the system comprises a flexible tether configured to be towed behind an airborne mother ship. A drag device is secured to a distal end of the flexible tether to generate drag and maintain tension in the flexible tether. A reel associated with the mother ship anchors a proximal portion of the flexible tether and selectively lets out and takes up the flexible tether to adjust a length of the flexible tether. A capture mechanism associated with the aircraft engages the flexible tether to enable the aircraft to translate along the flexible tether. In embodiments of the present methods, a flexible tether is deployed from an airborne mother ship. An aircraft translates forward and rearward along the flexible tether. Prior to launch, the weight of the aircraft is transferred from the flexible tether to the wings. During recovery, the weight of the aircraft is transferred from the wings to the flexible tether. | 02-18-2010 |
| 20100163673 | METHOD AND APPARATUS FOR FAST DEPLOYING AND RETRIEVING OF TOWED BODIES - In a method and apparatus for controlling the deployment of a towline connecting a mooring craft to an ejected object comprising the steps of monitoring velocity to determine when a point for optimum braking has been achieved and then engaging a brake system to retard deployment of the towline, a DC motor augments and controls the brake system. The DC motor further controls the retrieval of the object. A cutter mechanism uses a first blade to grip the towing cable to maintain tension thereon as a second blade cuts the cable. A spring biased boom in combination with spring biased fins on the ejected object rapidly deploys the object from its storage housing. A locking mechanism secures the deployment mechanism in a stable locked position upon the object reaching its fully extended position. | 07-01-2010 |
| 20100276537 | SYSTEM AND METHODS FOR AIRBORNE LAUNCH AND RECOVERY OF AIRCRAFT - A system and methods for airborne launch and recovery of aircraft. In one embodiment the system comprises a flexible tether configured to be towed behind an airborne mother ship. A drag device is secured to a distal end of the flexible tether to generate drag and maintain tension in the flexible tether. A reel associated with the mother ship anchors a proximal portion of the flexible tether and selectively lets out and takes up the flexible tether to adjust a length of the flexible tether. A capture mechanism associated with the aircraft engages the flexible tether to secure the aircraft to the flexible tether. In certain embodiments of the present methods, a flexible tether is deployed from an airborne mother ship. An aircraft translates forward and rearward along the flexible tether. Alternatively, the aircraft translates forward and rearward as the flexible tether taken up and let out from the mother ship. Prior to launch, the weight of the aircraft is transferred from the flexible tether to the wings. During recovery, the weight of the aircraft is transferred from the wings to the flexible tether. | 11-04-2010 |
| 20100288877 | DECOY PROTECTION SYSTEM FOR AIRCRAFT AND METHOD OF PROTECTION - The current invention is inclusive of a decoy protection system and method of protecting jet aircraft from shoulder fired missiles comprising while such aircraft is in a flight envelope where it is susceptible to being hit by a such a missile, by employing a decoy means towed by aircraft at a distance away from the aircraft whereby the decoy means is located sufficiently remote away from any part of said aircraft that a missile strike on the decoy mean will not normally damage the aircraft, supplying said decoy means with jet fuel from said aircraft and burning said jet fuel in the decoy means to create a high intensity IR signature in the decoy means sufficient to divert shoulder fired missiles from said aircraft to said decoy means. | 11-18-2010 |
| 20110068223 | Aircraft Decoy Arrangement - Aircraft decoy arrangement and method for generating a decoy signal from an aircraft having an isolated decoy. An aircraft receiver detects a threat signal from a threat source targeting the aircraft. An aircraft signal processor produces a decoy relay signal based on the threat signal, where the decoy relay signal frequency is significantly lower than the threat signal frequency and is slowly attenuated through air, the signal processor calibrating the decoy relay signal in accordance with a received test signal to compensate for inaccuracies. An aircraft transmitter transmits the decoy relay signal and an optional reference signal to the decoy, where it is received by a decoy receiver, converted back to a decoy signal by a decoy frequency converter, and transmitted by a decoy transmitter, causing the threat source to detect the decoy signal and lock onto the decoy rather than the aircraft. | 03-24-2011 |
| 20110139928 | AUTOGYRO AIR VEHICLE - An unmanned, towable aerovehicle is described and includes a container or frame to hold or support cargo, at least one and, in some examples, a plurality of autogyro assemblies connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container or frame includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly. In an example, the autogyro assembly includes a mast extending from the container, a rotatable hub on an end of the mast, and a plurality of blades connected to the hub for rotation to provide lift to the vehicle. In an example, an electrical motor rotates the blades prior to lift off to assist in take off. In an example, the electrical motor does not have enough power to sustain flight of the vehicle. The aerovehicle can further include plurality of autogyro assemblies to assist in flight. The aerovehicle can include surfaces that provide lift or control to assist in the flight profile of the aerovehicle. | 06-16-2011 |
| 20110174922 | UNGUIDED MISSILE AND PROJECTILE DEFENSE SHIELD SUPPORTED BY TETHERED BALLOONS - In this invention, there is provided a method and device for shielding and deflecting unguided missiles, mortars and other projectiles and ordnance. A plurality of lighter-than-air balloons are tethered from a plurality of ground anchors so that the balloons are positioned spaced apart, adjacent to, along and buoyed above the border to be defended between the launch area and the target area. A defense shield is suspended from the plurality of tethered lighter-than-air balloons, extending generally vertically covering a range of heights for engaging and deflecting missiles launched along the expected trajectories. | 07-21-2011 |
| 20110272522 | AIRBORNE TIME DOMAIN ELECTROMAGNETIC TRANSMITTER COIL SYSTEM AND APPRATUS - A tow assembly for an airborne electromagnetic surveying system, including: a transmitter coil frame supporting a transmitter coil, the transmitter coil frame being formed from a plurality of serially connected frame sections forming a loop, the transmitter coil frame having rotating joints at a plurality of locations about a circumference thereof enabling the transmitter coil frame to at least partially bend at the rotating joints; and a suspension assembly for towing the transmitter coil frame behind an aircraft, the suspension assembly being attached to the circumference of the transmitter coil frame at spaced apart locations. | 11-10-2011 |
| 20110278393 | AERODYNAMICALLY STABILIZED INSTRUMENT PLATFORM - A suspension apparatus for suspending instrumentation from an airborne platform may include a generally longitudinal boom having a payload end and a tail end. Yaw and pitch stabilizers may be disposed at the tail end of the boom. A mast that may be selectively translatable on the boom may connect the boom to a tether line of the airborne platform. The payload may be attached to the payload end of the boom. The mast may be positioned axially along the boom at the center of gravity of the combination of the payload, boom, pitch stabilizer, and yaw stabilizer. | 11-17-2011 |
| 20130062464 | TOWED SENSOR ARRAY MANEUVERING SYSTEM AND METHODS - A towed sensor array maneuvering system and methods are disclosed. A towed airborne vehicle comprising a sensor array is actively maneuvered via a plurality of surfaces coupled thereto. The surfaces are controlled such that a desired path is tracked based on and as a function of desired tracking parameters. | 03-14-2013 |
| 20130313359 | AEROVEHICLE SYSTEM INCLUDING PLURALITY OF AUTOGYRO ASSEMBLIES - An unmanned, towable aerovehicle is described and includes a container or frame to hold or support cargo, at least one and, in some examples, a plurality of autogyro assemblies connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container or frame includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly. In an example, the autogyro assembly includes a mast extending from the container, a rotatable hub on an end of the mast, and a plurality of blades connected to the hub for rotation to provide lift to the vehicle. In an example, an electrical motor rotates the blades prior to lift off to assist in take off. In an example, the electrical motor does not have enough power to sustain flight of the vehicle. The aerovehicle can further include plurality of autogyro assemblies to assist in flight. The aerovehicle can include surfaces that provide lift or control to assist in the flight profile of the aerovehicle. | 11-28-2013 |
| 20140183300 | TETHERED PAYLOAD SYSTEM AND METHOD - A vehicle, especially a maritime vessel, is provided with an autogyro drawn by a tether. The tether contains mechanical strengthening components that enable it to securely retain the autogyro to the vehicle. The tether also contains two electrical conductors carrying different phases of AC power to the autogyro, and four optical fibers carrying optical data signals to and from the autogyro electronic payloads and avionics control circuitry. Signal converters at ends of the tether convert a wide range of electrical or wireless signals to optical data signals for transmission along the tether, and then back into the original electrical signal format for use by the autogyro or vehicle electronics. | 07-03-2014 |
| 20140203139 | ADAPTIVE SOLAR AIRFRAME - Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes an expandable body having an aerodynamic cross-section that reduces parasitic air drag at any given thickness of the body, further being able to change its shape in flight in response to changes in the relative position of the sun; and a flexible solar PV system attached to the surface of the expandable body. | 07-24-2014 |
| 20150021433 | SYSTEM AND METHOD FOR A TOWABLE AND INFLATABLE RECREATIONAL DEVICE WITH A RETRACTABLE WIND FOIL - Our system and method for a towable and inflatable recreational device with a retractable wind foil. This towable and inflatable recreational device expands the existing field of art in the water sports recreational devices. | 01-22-2015 |
| 20150028156 | VARIABLE DRAG AREA TOW SYSTEM AND METHODS - A variable drag area tow system including a tow cable, and a variable drag area device having a variable projected area, the variable drag area device is configured to have a smaller projected area as the velocity of the variable drag area device with respect to a fluid increases. A method of maintaining tension on a tow cable, the method including deploying at a first velocity a variable drag area device having a variable projected area, increasing the first velocity to a second velocity, and decreasing the projected area of the variable drag area device as the first velocity is increased to the second velocity. | 01-29-2015 |
| 20150076284 | Methods and Systems for Transitioning an Aerial Vehicle Between Hover Flight and Crosswind Flight - A method may involve operating an aerial vehicle in a hover-flight orientation. The aerial vehicle may be connected to a tether that defines a tether sphere having a radius based on a length of the tether, and the tether may be connected to a ground station. The method may involve positioning the aerial vehicle at a first location that is substantially on the tether sphere. The method may involve transitioning the aerial vehicle from the hover-flight orientation to a forward-flight orientation, such that the aerial vehicle moves from the tether sphere. And the method may involve operating the aerial vehicle in the forward-flight orientation to ascend at an angle of ascent to a second location that is substantially on the tether sphere. The first and second locations may be substantially downwind of the ground station. | 03-19-2015 |
| 20150353194 | Methods and Systems for Transitioning an Aerial Vehicle Between Hover Flight and Crosswind Flight - A method may involve operating an aerial vehicle in a hover-flight orientation. The aerial vehicle may be connected to a tether that defines a tether sphere having a radius based on a length of the tether, and the tether may be connected to a ground station. The method may involve positioning the aerial vehicle at a first location that is substantially on the tether sphere. The method may involve transitioning the aerial vehicle from the hover-flight orientation to a forward-flight orientation, such that the aerial vehicle moves from the tether sphere. And the method may involve operating the aerial vehicle in the forward-flight orientation to ascend at an angle of ascent to a second location that is substantially on the tether sphere. The first and second locations may be substantially downwind of the ground station. | 12-10-2015 |
| 20160102654 | Tether Termination Systems and Methods - An Airborne Wind Turbine (“AWT”) may be used to facilitate conversion of kinetic energy to electrical energy. An AWT may include an aerial vehicle that flies in a path to convert kinetic wind energy to electrical energy. The aerial vehicle may be tethered to a ground station with a tether that terminates at a tether termination mount. In one aspect, the tether has a core and at least one electrical conductor. The tether core may be terminated at a first location in a tether termination mount along an axis of the termination mount, and the at least one electrical conductor may be terminated at a second location in the tether termination mount along the same axis that the core is terminated. This termination configuration may focus tensile stress on the tether to the tether core, and minimize such stress on the at least one electrical conductor during aerial vehicle flight. | 04-14-2016 |
