| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244013000 | Airplane sustained | 56 |
| 20090121074 | WING LOAD ALLEVIATION STRUCTURE - A wing load alleviation structure for use on an aircraft, comprising a front spar, wherein the front spar includes a plurality of alternating rigid spar structures and inflatable spar structures; and a rear spar, wherein the rear spar includes a plurality of alternating rigid spar structures and pivot joints, such that when a load is applied to the front and rear spars, deflection of each of the front and rear spars continues at a first rate until a critical load is reached, and then as the loading increases, deflection of each of the front and rear spars continues at a second rate. | 05-14-2009 |
| 20090206193 | Ballistically deployed telescoping aircraft wing - An apparatus for increasing an aerodynamic surface area of an aircraft, e.g., a wing thereof, includes coaxially disposed first and second elongated airfoils and an inflatable device arranged to move the first airfoil coaxially relative to the second airfoil. The second airfoil has a root end fixed to the vehicle and an opposite outboard end, and the first airfoil is arranged to move axially between a retracted position generally inboard of the outboard end of the second airfoil and a deployed position generally outboard thereof. When the movable airfoil is deployed, a latching mechanism locks it in position. The inflatable device can include a collapsible duct that is sealed at one end and coupled at a second end to an inflating source, such as a reservoir of a compressed gas or a pyrotechnic gas generator. | 08-20-2009 |
| 20100012767 | LIGHT MULTIPURPOSE AIRCRAFT - A light multi-purpose aircraft comprises a fuselage ( | 01-21-2010 |
| 20100051741 | Unmanned air vehicle - An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land. | 03-04-2010 |
| 20100237187 | INVERTED AIRFOIL PYLON FOR AN AIRCRAFT - An aircraft including a wing and a pylon, wherein the pylon provides an airfoil inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series LEARJET® is provided. The improvement includes an increased distance between a leading edge of a wing and an intake of an engine of the aircraft, which reduces drag and increases lift for improved flight dynamics of the aircraft. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamics of the aircraft. The method includes steps of removing an original engine from an original pylon, removing the original pylon from the fuselage of the aircraft, and mounting a new pylon in a new location adjacent to the fuselage, wherein the new location is aft of the original location. | 09-23-2010 |
| 20100282896 | FLYING ENTERTAINMENT VEHICLE - An apparatus for use as a flying entertainment vehicle. The apparatus includes a lift system, such as a parawing, that is inflated by air to generate lift and further includes a vehicle frame attached to the lift system such as by suspension lines that also space the lift system apart from the vehicle frame. The apparatus includes a thrust assembly supported on the vehicle frame that is operable to propel the vehicle at a flight speed at which the lift system is operated, e.g., the parawing is inflated, to generate lift to suspend the vehicle frame above the ground. The apparatus includes show elements that may be supported on or by the vehicle frame and be configured to be lift neutral. The show elements function to distract observers away from the lift system such as by appearing to provide the lift or features that cause the vehicle frame to fly. | 11-11-2010 |
| 20110114784 | HUMAN-POWERED, BIRD-LIKE WINGS FLYING DEVICE - The human-powered, bird-like flying device of the present invention has wings which may rotate around the keel and legs that let the pilot control rotation of the wings, which is to make the wings flap. The present invention develops one of the more efficient methods of ascending, which is to increase the angle of attack by moving the control bar forward while shifting the pilot's weight to efficiently strike onto the legs that make the wings flap downward. The present invention is secure and stable in the air, particularly while ascending and descending. This is done by selecting the proper shape and sail area of the wings and by proper attachment of the arm, legs and the hang loop, which hold the pilot's body. | 05-19-2011 |
| 20110133021 | SUPERSONIC AIRCRAFT WITH SHOCKWAVE CANCELING AERODYNAMIC CONFIGURATION - Disclosed is a supersonic aircraft design having a single structural component that simultaneously joins the wings to the aircraft fuselage, the engines to the aircraft fuselage, and the wings to the engines, resulting in an airframe planform, which, in combination aerodynamic shaping and structural morphing technologies within the aircraft fuselage, enables the aircraft to be optimized to reduce sonic boom. | 06-09-2011 |
| 20110155840 | MORPHING AIRCRAFT - A morphing aircraft that is achieves multi-modality location and camouflage for payload emplacement The morphing aircraft includes a substantially cylindrical fuselage including a shape configured as a packaging container with a first end and a second end A set of wings is coupled to the fuselage The set of wings includes a first position where the set of wings is extended outwards from the fuselage and a second position where the set of wings is retracted inwards towards the fuselage A tail is coupled to the second end of the cylindrical fuselage The tail includes a first position where the tail is extended outward from the fuselage and a second position where the tail is retracted inward towards the fuselage A propeller is mounted to the first end of the fuselage An engine is mechanically coupled to the propeller The engine is enclosed within the fuselage and powers the propeller. | 06-30-2011 |
| 20120104151 | POWERED PARAFOIL CARGO DELIVERY DEVICE AND METHOD - A powered parafoil device is disclosed. The device includes a main body provided with at least one thrust generator for imparting the main body thrust in a determined direction. The device is also includes a parafoil connected to the main body by cords attached to the main body at attachment positions, and a tilting mechanism for tilting the main body with respect to the parafoil, when airborne. The tilting mechanism is capable of tilting the main body between at least two states: in the first state the determined direction of the thrust is substantially parallel to the direction of flight of the device when airborne, and in the second state the determined direction of the thrust is tilted with respect to the direction of flight of the device when airborne, imparting the main body a thrust vector component in the vertical direction. A method for increasing lift of a powered parafoil device and methods for cargo delivery are also disclosed. | 05-03-2012 |
| 20120267472 | AIR VEHICLE - A sensor/emitter arrangement (M | 10-25-2012 |
| 20130168489 | Roadable, Adaptable-Modular, Multiphibious-Amphibious Ground Effect or Flying, Car-Boat-Plane or Surface-Effect Motorcycle - A roadable, adaptable-modular, multiphibious-amphibious ground-effect or flying, car-boat-plane or surface-effect motorcycle. A pivoting wing using the NACA 23112 airfoil provides longitudinal stability through changes in wing or power settings. The airfoil can also be “locked” in place to provide conventional aircraft type controls. The wings fold for driving mode or can be removed. Surface-effect sensor rods provide the automatic altitude control for operations in surface-effect mode. Horizontal stabilizer and elevator provide trim and balance to level the vehicle for passenger comfort and optimal landing attitude. The hull/fuselage consists of three main modules: The main central module (engine, transmission, passengers, wings and cargo storage), the forward module and the aft module which may include one or two wheels with or without a motor, engine, batteries or fuel and differential. | 07-04-2013 |
| 20130228645 | WING FOR AN UNMANNED AIRCRAFT - A single wing for an unmanned aircraft adapted for image acquisition, surveillance or other applications consists of a ribbed frame and a foam wherein the ribbed frame is integrated during molding for stiffness and strength. The foam has a container for holding the electric and/or electronic components. The foam constitutes the outer layer of the unmanned aircraft at impact side. The wing can be produced at low cost and low complexity in large volumes, increases the impact resistance and safety when used in civil areas, and is removable and disposable thereby enabling reuse of the electric and/or electronic components. | 09-05-2013 |
| 20130256451 | AIRCRAFT HAVING AT LEAST TWO AIRCRAFT FUSELAGES AND A FIRST WING ARRANGEMENT WITH AT LEAST TWO WING SECTIONS THAT ARE NOT CONNECTED TO EACH OTHER - An aircraft having at least two separate aircraft fuselages is provided. The aircraft includes a first wing arrangement with at least two non-connected wing sections, and a second wing. In each case the wing sections of the first wing arrangement extend from the outside of an aircraft fuselage towards the outside. The second wing is arranged between insides of the at least two aircraft fuselages. Connecting regions of the first wing arrangement and of the second wing are arranged so as to be offset relative to each other at least on an X-Z-plane of an aircraft-fixed coordinate system. Consequently, the first wing arrangement and the second wing do not influence each other as a result of downwash, and in addition it is possible to do without horizontal stabilizer units that generate downthrust. | 10-03-2013 |
| 20130277495 | DEVICE AND METHOD FOR INCREASING THE AERODYNAMIC LIFT OF AN AIRCRAFT - A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics. | 10-24-2013 |
| 20140014766 | Personal Aircraft - A flying apparatus permitting a human operator to lie in a prone position to control the flying apparatus is disclosed. The flight and power controls can be manipulated by the operator's hands and feet, allowing the operator to take off, land, and perform aerobatic maneuvers while in a prone position. The human operator is securely maintained in a prone position through the use of a four-point strap harness and a roll cage or hatch that securely locks over the cockpit with the operator in place. The aircraft will be capable of takeoff and landing from almost any runway due to all-terrain landing gear attached to the airframe. | 01-16-2014 |
| 20140191078 | Airplane Emergency Supplemental Braking System And Method - A system, an apparatus, and a method for an aerospace vehicle braking system for decelerating an aerospace vehicle on a landing surface. An arm is provided having a first portion connected to the aerospace vehicle and a second portion generally distal to the first portion. The second portion of the arm includes an engagement portion configured to engage the landing surface. The arm is movable between a first position, wherein the engagement portion is substantially disengaged from the landing surface, and a second position, wherein the engagement portion engages the landing surface with a force sufficient to significantly decelerate the aerospace vehicle. The engagement portion is configured to pivot with respect to the arm in response to the direction of travel of the aerospace vehicle upon the landing surface. An actuator is connected to the arm to selectively move the arm between the first position and the second position. | 07-10-2014 |
| 20140231578 | STABILIZED UAV PLATFORM WITH FUSED IR AND VISIBLE IMAGERY - Embodiments of the present invention relate to an unmanned aerial vehicle (UAV) and a method of use. The UAV may comprise a UAV platform designed around a sensor system. The UAV platform may adjust itself in order to stabilize the sensor system. The UAV platform may comprise front UAV wings, back UAV wings, and a payload chamber. The front UAV wings and back UAV wings may adjust themselves by rotating about a line approximately perpendicular to the UAV's flight line. The payload chamber may adjust itself by rotating about the UAV's flight line. The sensor system may be located in an optimal location on the UAV platform, for example, behind the nose as far back as the front UAV wings. The sensor system may comprise an infrared (IR) and a visible camera. | 08-21-2014 |
| 20140312164 | PORTABLE UNMANNED AIRCRAFT FOR NEAR-INSTANT AERIAL SURVEILLANCE - A portable unmanned aerial vehicle or aircraft, capable of being easily carried by a single individual by means of a mounting device, which can be fastened on a belt or strap. The aerial vehicle comprises a wing attached at one end to a fan or turbine assembly. The fan or turbine assembly may be electrically driven, with power supplied by one or more batteries. In flight, the fan or turbine assembly causes the aerial vehicle to rotate around its center-of-mass (COM), with lift provided by the wing as it rotates. A camera is located on the aircraft at or near the COM. | 10-23-2014 |
| 20140312165 | METHODS, APPARATUS AND SYSTEMS FOR AERIAL ASSESSMENT OF GROUND SURFACES - A hand-launched unmanned aerial vehicle (UAV) to determine various characteristics of ground surfaces. The UAV includes a lightweight and robust body/wing assembly, and is equipped with multiple consumer-grade digital cameras that are synchronized to acquire high-resolution images in different spectra. In one example, one camera acquires a visible spectrum image of the ground over which the UAV is flown, and another camera is modified to include one or more filters to acquire a similar near-infrared image. A camera mount/holder system facilitates acquisition of high-quality images without impacting the UAV's flight characteristics, as well as easy coupling and decoupling of the cameras to the UAV and safeguarding of the cameras upon landing. An intuitive user interface allows modestly trained individuals to operate the UAV and understand and use collected data, and image processing algorithms derive useful information regarding crop health and/or soil characteristics from the acquired images. | 10-23-2014 |
| 20140319266 | REMOTELY CONTROLLED MICRO/NANOSCALE AERIAL VEHICLE COMPRISING A SYSTEM FOR TRAVELING ON THE GROUND, VERTICAL TAKEOFF, AND LANDING - A microscale radio-controlled aerial micro-drone vehicle, having a fixed wing (as opposed to a rotary wing) having a propulsion device the vehicle including wheels for traveling on the ground, which are attached to the side ends of a section of the wing. The rotational axis Y1 of the wheels being located in front of the center of gravity of the micro-drone, the center of gravity of the micro-drone being located in front of the aerodynamic center of the micro-drone. The rotational axis Y1 of the wheels being aligned with the thrust axis of the propulsion device and the wheels are sized such that the radius D/2 thereof is greater than the distance between the rotational axis Y1 of the wheels and the trailing edge of the wing. | 10-30-2014 |
| 20140332620 | UNMANNED AERIAL VEHICLE - An unmanned aerial vehicle, comprising: a fuselage having a first side board and a second side board spaced apart and connected by at least one transverse board; the first side board, the second side board, and the at least one transverse board being printed circuit boards; at least one of the first side board, the second side board, and the at least one transverse board having formed and mounted thereon conductive traces and at least one component, respectively, for controlling and monitoring the unmanned aerial vehicle; first and second wings mounted to the fuselage; and, a tail mounted to the fuselage. | 11-13-2014 |
| 20150097071 | AIRBORNE KINETIC ENERGY CONVERSION SYSTEM - Methods and apparatus to harvest renewable energy are provided herein. In some embodiments, a wind-powered aircraft includes an airframe suitable for untethered flight in an open airspace; and an airborne kinetic energy conversion system attached to the airframe, the airborne kinetic energy conversion system comprising a turbine, a generator connected to the turbine, and an electrical storage means connected to the generator. | 04-09-2015 |
| 20150102156 | AIRCRAFT WING HAVING CONTINUOUSLY ROTATING WING TIPS - The present invention relates to a wing for an aircraft. The wing includes a main wing section extending from an inboard end to an outboard end along a lateral axis of the wing, the inboard end for connecting the main wing section to the aircraft. The wing also includes a wing tip having a proximal end and a distal end, the wing tip being rotatably mounted at the proximal end to the outboard end of the main wing section and arranged to freely rotate about a wing tip rotational centre with respect to the main wing section. | 04-16-2015 |
| 20150102157 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path. | 04-16-2015 |
| 20150108269 | HYPERSONIC AIRCRAFT - A supersonic aircraft having unique structural, geometrical, electromagnetic, mechanical, thermal and aerodynamic configuration is described. Its design characteristics maximize aerodynamic performance, speed, efficiency, comfort and range in the operational affect of carrying passengers over long distances at very high flight speeds and Mach numbers, generally above Mach 4.0+. It has fully integrated-mated fuselage twin engine nacelle structures which reduce and stabilize wave drag, wherein engines sit forward of the sonic boom electrode swept aerospace but are integrated right through the sub-wing, the aero-spike and inlet just above the top surface of the central wing, and above and the major wing mating join, attached via a massive composite titanium keel structure, through the central wing box and fuselage. | 04-23-2015 |
| 20160009363 | UN-MANNED AERIAL VEHICLE | 01-14-2016 |
| 20160046365 | AIRCRAFT WITH A NACELLE-HOUSED MAIN LANDING GEAR - A main landing gear for aircraft having a fuselage, a wing and a jet engine on opposite sides of the fuselage and housed in a nacelle attached to the wing. The main landing gear includes a landing gear at each side of the wing having wheels coupled to a driving device that moves the wheels between stowed and deployed positions. The engine nacelles each include a well located laterally with respect to the jet engines and configured as a housing space for stowing the wheels of the landing gears. | 02-18-2016 |
| 20160052619 | SIMPLIFIED INVERTED V-TAIL STABILIZER FOR AIRCRAFT - The simplified inverted V-tail aircraft comprise of fixed inverted V-tail stabilizers, wing mounted elevons, with no moving control surfaces attached to the fixed inverted V-tail stabilizers. Elevons act as elevators as well as aileron elements and rudders and the design is simplified, making construction far less costly. No control cables or other control devices are required to be routed to the inverted V-tail. Moreover, the number of control surfaces is reduced and limited to the wing portion of the aircraft. The inverted V-tail may thus be made in one piece, for example, using composites, thus simplifying construction considerably. | 02-25-2016 |
| 20160083075 | AIRCRAFT - An aircraft ( | 03-24-2016 |
| 20160096613 | VTOL SYMMETRIC AIRFOIL FUSELAGE OF FIXED WING DESIGN - Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system. | 04-07-2016 |
| 20160121995 | AIRCRAFT AND CONVERTIBLE WING ASSEMBLY - In at least some implementations, an aircraft includes a fuselage, a wing spar rotatably carried by the fuselage, a first wing element and a second wing element. The first wing element is carried by the wing spar, rotatable with the wing spar, and slidably moveable relative to the fuselage and wing spar. The second wing element is connected to the first wing element for pivoted movement of the second wing element relative to the first wing element. The second wing element at least partially overlaps the first wing element and the first and second wing elements are moveable to a plurality of positions wherein the amount that the second wing element overlaps the first wing element varies to vary the effective combined wing area of the wing elements. | 05-05-2016 |
| 20160144966 | AN AIRCRAFT INCLUDING AN ENGINE ATTACHMENT WITH A CONTROL SURFACE - An aircraft including a fuselage extending along a longitudinal axis and having a rear end pointing reward of the aircraft, a main gear connected to the fuselage in a main gear position with respect to the longitudinal axis, and an engine for propelling the aircraft provided outside of the fuselage and attached to the fuselage via an attachment device between the main gear position and the rear end, wherein the engine generates a repulsive air stream streaming in the reverse direction. A surface element is moveably connected to the attachment device. The surface element moves between a neutral position at which it does not deflect the repulsive air stream, and a deflected position at which it deflects the repulsive air stream to assist aircraft rotation during take-off. | 05-26-2016 |
| 20160144969 | SOLAR POWERED AIRPLANE - A solar powered aircraft including a modular main wing and a pair of relatively large modular winglets attached to the transverse end portions of the main wing. To collect solar radiation, including relatively low-angle radiation, solar panels are mounted to both the main wing and the winglets. In some embodiments, the aspect ratio of the main wing is relatively low, such as between 9 and 15, i.e., the main wing is relatively deep compared to its wing span. In some embodiments, the winglets are relatively long, such as in the range of 0.2 to 0.7 times the length of the main wing semi-span. In some embodiments, a truss-like spar passes through and helps support the wing and the winglets. | 05-26-2016 |
| 20160152315 | AIRCRAFT FUSELAGE FRAME | 06-02-2016 |
| 20160152318 | AEROSPACE PLANE SYSTEM | 06-02-2016 |
| 20160185445 | ELEVON CONTROL SYSTEM - A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements. | 06-30-2016 |
| 20160375981 | ASYMMETRIC AIRCRAFT AND THEIR LAUNCH AND RECOVERY SYSTEMS FROM SMALL SHIPS - An asymmetric aircraft ( | 12-29-2016 |
| 244015000 | Fluid propelled | 10 |
| 20090065632 | AIRCRAFT WITH JET ENGINES ARRANGED AT THE REAR - When an aircraft is propelled by at least one jet engine fixed in a rear part of the aircraft, at least one substantially horizontal rear aerodynamic surface, the rear horizontal surface, is arranged at the rear of the aircraft and at least one jet engine is fixed under the rear horizontal surface by an attachment mast fixed by its upper part to the rear horizontal surface and maintains, by its lower part, the jet engine. The rear horizontal surface is also the horizontal tail unit of the aircraft or a horizontal surface maintained above the fuselage. The rear surfaces and the fuselage are arranged such that the engines are installed and removed using a vertical movement of the engines, which are advantageously one, two or three in number, in the rear zone of the aircraft. | 03-12-2009 |
| 20090072077 | High passenger capacity airplane - A high capacity passenger airplane is provided with a plurality of fuselages releasably mounted on it wings section. Each fuselage has an outer shell with a plurality of passenger cabins mounted in tandem with the shell. The passenger cabins are equipped with sliding wheels such that they may be discharged through a rear exit door of the fuselage to separate from the airplane in accident. Each passenger cabin is equipped with safety parachutes and external safety air bags at its underside such that it may be safely landed on ground or on water after having discharged from a fuselage. | 03-19-2009 |
| 20090108125 | SYSTEMS AND METHODS FOR CONTROL OF ENGINE EXHAUST FLOW - Coanda Effect and lift produced along a surface of an airfoil are increased by ducting compressed fluid from the engine to the surface of the airfoil. An engine produces exhaust gases that are predominantly directed toward an aft end of the aircraft by a cowling or other structure as an exhaust plume. One or more internal ducts extend from the engine to the surface of the airfoil to thereby transmit a compressed fluid from the engine to the surface in order to suppress flow separation along the surface, thereby causing the engine exhaust flow to remain attached to the surface over a wider span. Such structures and techniques may find particular use in aircraft designed to exploit upper surface blowing (USB) techniques and structures for short takeoff and landing (STOL) performance. | 04-30-2009 |
| 20090184195 | Hydrazine Monopropellant Decomposition Air Turboprop Engine - An engine for use in operating an aircraft is disclosed, the engine comprising a decomposition chamber configured to decompose into at least one combustible constituent element a first chemically unstable substance in the presence of a catalyst, wherein the decomposition of the first chemically unstable substance releases a first amount of heat; a first turbine configured to accept the constituent elements and the first amount of heat from the decomposition chamber and thereby rotate; a compressor rotationally connected to the first turbine, and configured to compress air when the first turbine rotates; and a combustion chamber configured to accept the compressed air and constituent elements and combust the combination, substantially regardless of an altitude above sea level and ambient air pressure, and output the combustion products into a power turbine, causing it to rotate, whereby the rotation of the first turbine and/or the power turbine rotate a propeller rotationally coupled to the first and power turbines. Alternately, a nozzle can be used in place of the power turbine, thereby creating a jet engine. | 07-23-2009 |
| 20090302150 | TUBULAR AIR TRANSPORT VEHICLE - An air transport vehicle of the present invention comprises a tubular body, said body comprising an upper half and a lower half. The upper half is positioned above the lower half and connected thereto. A central bore is formed between the upper half and the lower half. The bore extends longitudinally from the nose end of the vehicle to the tail end of the vehicle. The vehicle also comprises at least one propulsion device, preferably positioned inside the bore. The vehicle further comprises at least one bulkhead. The bulkhead connects the upper half to the lower half, and extending longitudinally inside the bore, thus dividing the bore into parallel subsections. In preferred embodiments, the upper half and the lower half comprise cavities, used among other things, for cargo and passenger transport. | 12-10-2009 |
| 20100096491 | ROCKET-POWERED ENTERTAINMENT VEHICLE - A rocket-powered vehicle used for entertainment, namely races, exhibitions, competitions, and revenue-generating events. | 04-22-2010 |
| 20120111994 | CROSS-FLOW FAN PROPULSION SYSTEM - The present invention includes improvements to cross-flow fans and cross-flow fan propelled aircraft including improved control, a dynamically adjustable vortex wall and internal housing, a vortex tube, vertical takeoff and landing rotorcraft configurations, the inclusion of an optimized oscillating blade fan, a wavy vortex wall, power plant refinements, dual leading and trailing edge configurations, stability improvements, tip plates, tapered wings, tapered fans, a fan construction method, and underwater applications. | 05-10-2012 |
| 20120325957 | ULTRA-RAPID AIR VEHICLE AND RELATED METHOD FOR AERIAL LOCOMOTION - The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB | 12-27-2012 |
| 20160016652 | AERIAL VEHICLES AND METHODS OF USE - An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings. | 01-21-2016 |
| 20160152341 | AIRCRAFT | 06-02-2016 |
| 244016000 | Glider | 8 |
| 20080223980 | BUBBLE GLIDER - This invention is a “bubble glider” which is a modified hybrid of the hot-air balloon and the glider. It has a distinct undulating forward motion. A simple bubble glider has a soft air-bubble, a hard air-bubble and a thin body and is made of 0.25 mm PVC sheets. It is used inside a completely sealed water tank with an external control unit. An operator uses the control unit to vary the buoyancy of the soft air-bubble and completely control the motion of the bubble glider. Specifically, the glider can glide forward and backward, change direction, take off and land vertically, float motionless and so on. In generalization, bubble gliders can be of many shapes and sizes, and made of, practically, any material. They can be designed to operate in totally closed containers or in open environments such as open water tanks, reservoirs, lakes, oceans and skies. | 09-18-2008 |
| 20080223981 | GROUND EFFECT GLIDER - A glider including a center section configured to receive and support an operator thereon, and a pair of air-foil shaped wings extending generally outwardly from the center section. The glider is configured such that when the glider supports the operator thereon the glider is glidable down an incline in the ground effect zone of the incline, and is configured such that the glider cannot sustainably glide above the ground effect zone. | 09-18-2008 |
| 20090272840 | AIRCRAFT FLIGHT TERMINATION SYSTEM AND METHOD - An aircraft has a flight termination system that allows flight of an unmanned aircraft to be quickly and efficiently terminated. The flight termination system separates one of the control surfaces of the aircraft, such as a wing, from a fuselage of the aircraft, while one or more other control surfaces connected to the fuselage. The separation may be accomplished by firing one or more explosive bolts to release a clamp that connects the control surface to the fuselage. The separation causes an asymmetry in configuration that results in a rapid crash of the aircraft. The flight termination system causes termination to be effected in small flight footprint, without use of powerful explosives, and without a large cost in weight or volume. The flight termination system may be used in unpowered or powered aircraft. | 11-05-2009 |
| 20100001122 | SPAR FOR SAILWINGS - A sail wing for a lightweight aircraft comprising a membrane; a front spar; and a tensioned rear wire attached to a trailing edge of the membrane, such that when the front spar is bent to match a curve of the tensioned trailing edge of the sail wing membrane, the sail wing membrane has substantially little or no twist, and results in substantially little or no induced drag. | 01-07-2010 |
| 20110226891 | Airplane and space shuttle ejection seat - Ejection seats have been on the road towards perfection ever since they were first made. But there are still too many situations that can't be avoided with just one function, ejecting and parachuting down. We have attempted to take it a few steps further: adding a small jet pack and glider wings. This way, pilots and astronauts can apply it in their emergency escape routines. Using the small jet pack, astronauts can push themselves on their way back to the blue planet and pilots can get themselves out of a danger zone quickly. This can also be a wonderful outdoor sport or activity. | 09-22-2011 |
| 20120018568 | Ram Air Rigid Structure Glider - The present invention is a ram air rigid structure glider, which uses both ram air inflation and a rigid structure in order to produce the necessary aerodynamic lift to glide through the air. The frame uses two main structural beams, the spar and the keel, to form the general shape of the wings and the tail. The hubs and the network of lines expand the structure laid out by the spur and the keel. The hubs are evenly placed along the spur, and the network of lines are connected and crisscrossed in between the hubs. The sail is a piece fabric wrapped around the frame and has a plurality of cells, which are evenly spaces throughout the sail. The plurality of cells allows the sails to be inflated by ram air pressure. The pilot pod carries the user in the supine position and is attached to the frame. | 01-26-2012 |
| 20130284853 | Partially-Inflated Rigid-Structure Glider - A partially-inflated rigid-structure glider is a portable or collapsible gliding apparatus that a user can transport in a carrying case. The gliding apparatus includes a rigid yet collapsible frame, tension membranes over both on the wings and tail, and inflatable bladder, a pair of drogue brakes, and a left and right steering mechanism. The pair of drogue brakes is located on opposing sides of the gliding apparatus and create drag on its respective side in order to turn the gliding apparatus either left or right. The user can activate either drogue brake with the left and right steering mechanism, which are control lines attached to each drogue brake. The tension membranes are fitted over the frame so that the gliding apparatus has an airfoil shape in order to create lift with the wings and tail while the gliding apparatus is in flight. | 10-31-2013 |
| 20130299627 | Low speed, high performance hang glider - Sail deflection, from large resultant moments, creates excess aerodynamic twist and limits hang glider performance. Incorporating a rear spar and sail attachment system, as a design feature, allows control and definition of this critical performance component. Hang gliders with this design feature will produce more total lift which in turn will produce lower stall speeds and less drag. | 11-14-2013 |
