| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244130000 | Aerodynamic resistance reducing | 60 |
| 20080290218 | PLASMA ACTUATOR SYSTEM AND METHOD FOR USE WITH A WEAPONS BAY ON A HIGH SPEED MOBILE PLATFORM - A system and method for controlling a freestream air flow over a surface of an airborne mobile platform, for example an aircraft. In one implementation the system includes a plurality of plasma actuators used on an undersurface of a fuselage of an aircraft upstream of a weapons bay of the aircraft. When the plasma actuators are energized an induced flow is created adjacent the actuators. The induced flow operates to deflect the shear layer created when the freestream air flow moves over the weapons bay (while the bay doors are open), away from the weapons bay. This significantly reduces the oscillating acoustic pressure waves that would normally be produced if the shear layer turns into the weapons bay. The system and method significantly reduces acoustic noise inside the weapons bay and improves separation of ordnance from the weapons bay. | 11-27-2008 |
| 20090045289 | Flow-driven oscillating acoustic attenuator - An apparatus for attenuating acoustic resonance generated by flow over a cavity in a surface comprises a plurality of flat flaps proximate to an upstream edge of the cavity. The flaps are disposed in an array spaced in a width direction of the cavity edge, and are oscillated by the flow in two degrees of freedom solely by the flow, independent of an actuation mechanism. Each flap includes a first hinge generally coextensive with the surface for enabling oscillation in a first degree of freedom and a second hinge orthogonal to the first hinge and forming a tab for enabling oscillation in a second degree of freedom. The hinges are constructed with torsional spring constants that provide predetermined oscillation frequencies and magnitudes. The apparatus can include a deployment mechanism for moving each flap between a stowed position wherein it is generally flush with the surface and a deployed position wherein the flap can be oscillated by the flow. | 02-19-2009 |
| 20090065645 | Articles with reduced fluid dynamic drag - A fluid dynamic article includes a treated surface | 03-12-2009 |
| 20090121083 | Nacelle Flow Assembly - A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plurality of holes are disposed on the cowl. Each of the plurality of holes are configured to alter local air pressure about one of the first surface and the second surface of the cowl. The plurality of holes are in communication with the flow volume. | 05-14-2009 |
| 20090321572 | FAIRING AND AIRFOIL APPARATUS AND METHOD - An airfoil for use on a high speed, jet powered airborne mobile platform and secured to an exterior surface of said mobile platform at a location so as to be disposed within a boundary layer during flight of the mobile platform. The airfoil produces a peak Mach number for airflow over a longitudinal centerline of said airfoil that is no greater than about Mach 1.2 when said mobile platform is moving at a speed of about Mach 0.85 with a relative constant Mach number flow over a region defined as at least an approximate 20% length of maximum thickness of said airfoil. The airfoil also has a pressure distribution (Cp) that is positive at a trailing edge thereof. | 12-31-2009 |
| 20090321573 | Rotor/wing dual mode hub fairing system - A hub fairing system ( | 12-31-2009 |
| 20100038488 | ANTENNA FAIRING AND METHOD - A fairing suitable for enclosing a component mounted on an exterior surface of a mobile platform, and more particularly on an outer surface of a high speed mobile platform such as a jet aircraft or an aerospace vehicle. The fairing provides aggressive closure angles for optimum RF performance when used to house an antenna that is scanned to varying azimuth and elevation angles. The fairing further provides low aerodynamic drag, is scalable to enclose components having wide ranging dimensions, and provides attached flow with minimum separation of airflow thereover for airflows experienced by high speed jet aircraft, and reduces or eliminates RF reflections within the fairing from the RF beam of the antenna. | 02-18-2010 |
| 20100065687 | Aircraft structure - An aircraft structure comprising: a spar; a primary cover attached to the spar and extending on a first side of the spar; and a secondary cover positioned on a second side of the spar and partially overlapping an internal surface of the primary cover. A bracket is attached to the spar, and a spacer is provided between the secondary cover and the bracket. The spacer is sized so that the primary and secondary covers together form a substantially continuous external aerodynamic surface. The structure provides an alternative to conventional butt-strap arrangements. | 03-18-2010 |
| 20100108813 | PASSIVE DRAG MODIFICATION SYSTEM - A micro-array surface that provides for drag reduction. In one aspect, an aerodynamic or hydrodynamic wall surface that is configured to modify a fluid boundary layer on the surface comprises at least one array of micro-cavities formed therein the surface. In one example, the interaction of the micro-cavities with the boundary layer of the fluid can delay transition of the fluid over an identical smooth surface without the micro-cavities. | 05-06-2010 |
| 20100170993 | Aerodynamic Fairing for aircraft lift strut - An aerodynamic fairing for the lift strut of an aircraft is disclosed. The fairing has an airfoil shape on the outside specially chosen to minimize aerodynamic drag. It has a thin external skin and an internal structure of foam material to provide stiffness and to allow its secure attachment around the existing lift strut. Special fillets are provided at either end of the fairing to assure a smooth transition of the fairing to the adjacent fuselage and wing undersurface to further minimize aerodynamic drag. The fairing is split at its trailing edge, allowing installation and removal by a standard aircraft fastener integrated in the fairing's trailing edge. | 07-08-2010 |
| 20100170994 | ELASTIC AIRCRAFT JOINT FAIRING - A method and apparatus comprising an adhesive layer and a conductive elastic material layer. The adhesive layer is capable of being placed in a channel for a joint. The adhesive layer is capable of resuming an original shape after being deformed. A conductive elastic material layer is on the adhesive layer. The coating covers the conductive elastic material layer and is capable of resuming the original shape after being deformed. | 07-08-2010 |
| 20100187359 | RIGID TIPPED RIBLETS - A multilayer construction for aerodynamic riblets includes a first layer composed of a material with protuberances, the first layer material exhibiting a first characteristic having long-term durability and a second layer composed of a material, exhibiting a second characteristic with capability for adherence to a surface. | 07-29-2010 |
| 20100187360 | SHAPE MEMORY RIBLETS - A multilayer construction for an array of aerodynamic riblets incorporates a first layer composed of a material with protuberances, the first layer material having shape memory and a second layer composed of a material exhibiting a second characteristic with capability for adherence to a surface. | 07-29-2010 |
| 20100187361 | AMORPHOUS METAL RIBLETS - An array of aerodynamic riblets is created by a plurality of high stiffness tips with a layer supporting the tips in predetermined spaced relation and adhering the tips to a vehicle surface. | 07-29-2010 |
| 20100200698 | FUSELAGE AND A METHOD FOR REDESIGNING IT - The invention relates to aircraft engineering for improving aerodynamic quality of helicopters, aeroplanes, including traditionally designed airbuses and amphibian airplanes, aerodynamic ground-effect and air-cushion vehicles, possibly by redesigning said transportation means. Flying drag is reduced, possibly by redesigning aircraft, helicopters, ground-effect crafts and air-cushion vehicles. Result is achievable by reducing a contacting area between the external surface of fuselage tail section and a high-speed air flow. Contacting area is reduced by increased area of orifices in fuselage tail section. To increase lifting force without increasing pressure resistance, the aerodynamic channel bottom is designed convex upwards, for example curved upwards along the shape of convex side of airfoil section. The aerodynamic channel skin top orifice can be located under tail fin middle part and lengthwisely divided by said fin to the right and left, for example in two. Redesign enables reducing fuselage total drag, reducing required engine thrust. | 08-12-2010 |
| 20100219296 | REDUCED DRAG SYSTEM FOR WINDMILLS, FANS, PROPELLERS, AIRFOILS, AND HYDROFOILS - Airfoil and hydrofoils systems with structures having a surface texture defined by fractal geometries are described. Raised portions or fractal bumps can be included on the surfaces, forming a surface texture. The surface textures can be defined by two-dimensional fractal shapes, partial two-dimensional fractal shapes, non-contiguous fractal shapes, three-dimensional fractal objects, and partial three-dimensional fractal objects. The surfaces can include indents having fractal geometries. The indents can have varying depths and can be bordered by other indents, or bumps, or smooth portions of the airfoil or hydrofoil structure. The fractal surface textures can reduce vortices inherent from airfoil and hydrofoil structures. The roughness and distribution of the fractal surface textures reduce the vortices, improving laminar flow characteristics and at the same time reducing drag. The systems are passive and do not require applied power. | 09-02-2010 |
| 20100282907 | SEALING SYSTEM FOR THE GAP EXISTING BETWEEN THE FUSELAGE AND THE ELEVATOR OF THE ORIENTABLE HORIZONTAL STABILISER OF AN AIRCRAFT, EXTENDED WITH AN AERODYNAMIC FAIRING FOR SEALING OF THE OPENING EXISTING BETWEEN THE FUSELAGE AND THE ORIENTABLE HORIZONTAL STABILISER - Sealing system for the gap ( | 11-11-2010 |
| 20100282908 | Methods for Reducing Laminar Flow Disturbances on Aerodynamic Surfaces and Articles having Self-Cleaning Aerodynamic Surfaces - Aircraft aerodynamic surfaces coated with photocatalytic self-cleaning coating reduces the need for washing off insects and other organic contaminants. Disturbances in laminar flow profiles due to organic contaminants are reduced, thereby improving performance by reducing drag. The photocatalytic self-cleaning coating includes nano-particles of titanium oxide and may be applied using a sol-gel process. | 11-11-2010 |
| 20100282909 | ELASTOMERIC RIBLETS - An array of aerodynamic riblets incorporates a high elongation elastomeric layer having spaced tips and optionally a protective cladding. The elastomeric layer may be adhered to an aerodynamic surface directly or as an appliqué in combination with one or more of an adhesive layer, one or more supporting polymer layers and a metal foil layer. | 11-11-2010 |
| 20100308169 | AIRCRAFT WIRE FAIRING - A fairing has a moulded body and an electrical wire embedded therein. The body may be constructed from a moulded plastics material or a composite material. | 12-09-2010 |
| 20100320325 | Skin Panel Joint for Improved Airflow - An apparatus may comprise a first skin panel having a first surface, a second skin panel having a second surface, a first flange located at an end of the first skin panel, a second flange located at an end of the second skin panel, and a strip having a third surface. The first skin panel may be located adjacent to the second skin panel such that the first flange and the second flange form a channel. The strip may be bonded in the channel. Fluid flow over the third surface of the strip, the first surface of the first skin panel, and the second surface of the second skin panel may have a desired state. | 12-23-2010 |
| 20100320326 | KIT FOR MODIFYING A STRUT OF AN AIRCRAFT WITH AN AERODYNAMIC COVER - A kit for modifying a strut of an aircraft with an aerodynamic cover includes a rigid sheath formed from a first portion and a second portion. Each of the first portion and the second portion have a curved shape. The rigid sheath includes an angled leading edge and an angled trailing edge. Convex surfaces connect the leading edge and the angled trailing edge. There is an attachment for attaching the rigid sheath to the strut, the attachment securing the sheath to the strut such that the strut is positioned at the camber of the rigid sheath. | 12-23-2010 |
| 20100327115 | AIRCRAFT POD STORE SEPARATION CHARACTERISTICS - A method for modifying the flow field about an aircraft instrumentation pod to improve the separation characteristics of stores released from adjacent pylons includes measuring the flow field about the aircraft instrumentation pod to obtain measured flowfield data, examining the flowfield data measured about the aircraft instrumentation pod to detect regions of supercritical flow, analyzing the measured flowfield data to determine one or more causes for detected regions of supercritical flow about the instrumentation pod, and modifying the geometry of the instrumentation pod to reduce the effects of the any supercritical flow fields. In one application of the inventive method, the trailing end of an instrumentation pod was modified from a tapered end to form an ogive which reduced shocks formed about the pod at transonic speeds that interfered with the trajectory of stores released from adjacent pylons. | 12-30-2010 |
| 20110036947 | COATING SYSTEM FOR AIRCRAFT AND AIRCRAFT COATED THEREWITH - An aircraft having aerodynamic surfaces coated with a clear coat may be more easily cleaned and be more resistant to solvent degradation to the aircraft's paint. Such a clear coat is one having been prepared using a resin formulation including an aliphatic methacrylate and a curing agent, wherein the clear coat passes the SKYDROL Test. | 02-17-2011 |
| 20110042518 | VORTEX GENERATOR FOR FLUSH AIR INLETS PERFORMANCE IMPROVEMENT - A VG (vortex generator) placed on a body surface (aircraft or similar), upstream of a flush air inlet, in order to generate vortexes that will sweep away the boundary layer in front of the inlet, inducing a downwash effect in the freestream airflow, such VG consisting of a wing ( | 02-24-2011 |
| 20110073710 | STRUCTURALLY DESIGNED AERODYNAMIC RIBLETS - An array of aerodynamic riblets is formed with a surface layer for adhering to an aerodynamic surface and a plurality of riblet tips having a parabolic cross section extending from the surface layer. | 03-31-2011 |
| 20110147525 | SEALING OF AIRFLOW BETWEEN A WING AND A FUSELAGE - A sealing ( | 06-23-2011 |
| 20110186685 | Thin-Film Composite Having Drag-Reducing Riblets and Method of Making the Same - A film composite having generally parallel riblets reduces drag on the flow of fluid over a surface and may either be directly applied onto a substrate or secondarily bonded as an appliqué. The film composite is formed on a substrate layer by layer by sequentially assembling layers of a binder and an inorganic filler. | 08-04-2011 |
| 20110198444 | AERODYNAMIC STRUCTURE HAVING A RIDGED SOLAR PANEL AND AN ASSOCIATED METHOD - Air vehicles and associated aerodynamic structures are provided which include ridged solar panels to both reduce the drag and increase the solar energy harvested by the solar panel. The air vehicle may include an airframe and a solar panel carried by the airframe and defining an exterior surface thereof. The solar panel may include a plurality of ridged structures extending in a lengthwise direction. The ridged structures may be arranged such that a majority of the airflow over the exterior surface flows in the lengthwise direction. The plurality of ridged structures may include a plurality of lengthwise extending projections spaced about by respective valleys. | 08-18-2011 |
| 20110204185 | AIRCRAFT FAIRING - A shock control fairing for mounting a junction between adjoining aircraft surfaces. The fairing has a cross-sectional profile which varies along the length of the fairing. The cross-sectional profile of the fairing has a maximum area at a location which, when mounted to an aircraft, is substantially proximal to a location on the surface of the aircraft at which a shock would be expected to develop without the fairing. | 08-25-2011 |
| 20120068016 | AERODYNAMIC FAIRING DEVICE, AIRCRAFT COMPONENT ARRANGEMENT WITH AN AERODYNAMIC FAIRING DEVICE AND METHOD FOR INSTALLING SUCH A FAIRING PART - A fairing device for creating an aerodynamic cover for an area of an aircraft structure, including a first fairing part with an outer side forming a first exterior flow contour, and having a fairing section for contacting a first section of the aircraft structure and a connecting section. The first fairing part includes a mounting device for receiving a connecting element. The fairing device includes a second fairing part including a fairing section having an outer side forming a second exterior flow contour and is designed for contacting a second section of the aircraft structure and a connecting section. The shape of the outer side of the second fairing part is adapted to the inner side of the connecting section of the first fairing part in an overlapping area, so the connecting section of the first fairing part forms a joint piece protruding over the second fairing part in the overlapping area. | 03-22-2012 |
| 20120126061 | GAS EXHAUST DIVERTER - An aircraft comprises an outer aerodynamic surface and an exhaust duct having an opening in the outer aerodynamic surface. The duct has a duct wall curved at the opening so as to blend with the aerodynamic surface downstream of the duct. At least one fixed flow diverter is provided for diverting high temperature exhaust gas exiting the duct away from the aerodynamic surface immediately downstream of the duct opening. The curved duct wall provides low aerodynamic drag in cruise. The flow diverter(s) give aircraft designers freedom in terms of where the duct opening can be positioned without compromising the structural integrity of the aircraft through excessive heating of the aerodynamic surface immediately downstream of the duct opening. | 05-24-2012 |
| 20120132752 | INTERFACE ARRANGEMENT BETWEEN TWO COMPONENTS OF AN AIRCRAFT STRUCTURE USING A SEALING PART - Interface arrangement between a first component ( | 05-31-2012 |
| 20120175463 | Fuel Range For An Aircraft - An apparatus and method for improving the fuel range of an aircraft are provided. The aircraft includes a fuselage with a front windshield, and an external skin providing a top cover for a cockpit of the aircraft. The apparatus includes an aerodynamic fairing secured adjacent the windshield and enclosing the external skin covering the cockpit for a reduction in an abrupt change in area encountered by air flowing along the length of the fuselage. An enclosure is formed between the aerodynamic fairing and the external skin in which a fuel bladder, configured with a reticulated polyurethane foam insert, may be disposed for added fuel capacity of the aircraft. The method includes steps of providing an aerodynamic fairing configured to balance the flow of fluid over the aircraft during flight, and securing the aerodynamic fairing atop the aircraft and adjacent the front windshield. | 07-12-2012 |
| 20120234975 | FAIRING TRANSITION AND VEHICLE WITH A MOVABLE BODY AND A FIXED BODY COMPRISING A FAIRING TRANSITION - A fairing transition is provided for covering a gap between a movable body and a fixed body on a vehicle that includes, but is not limited to a base plate that is attachable to a vehicle, a cover plate that is attachable to the base plate. The base plate and the cover plate include, but are not limited to a correspondingly formed connecting profile having positive fit on surfaces that face each other, with the connecting profile configured to slide the cover plate onto the base plate. Furthermore, the cover plate is lockable to the base plate in an end position. | 09-20-2012 |
| 20120248248 | System and Method for Affixing Gateboxes to an Aircraft - A system for affixing a gatebox to an aircraft includes a first type of gatebox operable to release material from an aircraft, a second type of gatebox operable to release material from the aircraft, a frame coupled to the aircraft operable to receive a selected one of the first type of gatebox and the second type of gatebox; and a plurality of fastenings operable to secure the selected one of the first type of gatebox and the second type of gatebox to the frame. | 10-04-2012 |
| 20120312923 | MITIGATING TRANSONIC SHOCK WAVE WITH PLASMA HEATING ELEMENTS - Systems and methods for enhancing operations of an aircraft may include a plasma generator, a sensor, and a controller. The plasma generator may be positioned on an exterior of the aircraft such that it can provide localized heating thereon. The sensor may be configured to sense and transmit information regarding a transonic flight condition such as speed to the controller. The controller may be configured to activate the plasma generator in response to information from the sensor, so as to mitigate a transonic shock wave through localized heating. | 12-13-2012 |
| 20130001362 | ARRANGEMENT OF AERODYNAMIC AUXILIARY SURFACES FOR AN AIRCRAFT - An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced. | 01-03-2013 |
| 20130062469 | SURFACE ENTITY FOR THE REDUCTION OF THE AIR RESISTANCE OF AN AVIATION VEHICLE - The invention concerns a surface entity for the reduction of the air resistance of an aviation vehicle, in particular an aircraft. | 03-14-2013 |
| 20130193270 | STRUCTURALLY DESIGNED AERODYNAMIC RIBLETS - An array of aerodynamic riblets is formed with a surface layer for adhering to an aerodynamic surface and a plurality of riblet tips having a parabolic cross section extending from the surface layer. | 08-01-2013 |
| 20130214094 | NOSE FOR SUPERSONIC FLYING OBJECT - Provided is a nose for a supersonic flying object, which has a natural laminar flow nose shape capable of suppressing laminar-turbulent transition and drastically reducing a frictional drag. The nose for a supersonic flying object has a low resistive body shape symmetrical about a central axis as a base shape, wherein the base shape is approximately a cone shape having a linear, simple convex curve, or simple concave curve generatrix and a deformation element having a wavy shape is added to the base shape. | 08-22-2013 |
| 20130221157 | AIRCRAFT ENGINE PYLON AFT AERODYNAMIC FAIRING - An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end. | 08-29-2013 |
| 20130264425 | SEPARABLE STREAMLINED NOSE CONE FOR A GUIDED MUNITION, AND GUIDED MUNITION INCLUDING SUCH A NOSE CONE - A separable ejectable protective nosecone for a guided munition comprises a munition body of cylindrical shape of longitudinal axis ZZ′ having a munition body front end comprising a central part intended to be directed toward a target of the munition. The nosecone comprises, at the munition body front end and covering said front end, n contiguous nosecone portions of the same shape distributed about said longitudinal axis ZZ′, one respective pyrotechnic device per nosecone portion. Each of the pyrotechnic devices comprises a pyrotechnic device body secured to the munition body, a pusher piston in contact with the respective nosecone portion. Simultaneous activation of the n pyrotechnic devices separates the edges of the nosecone portions from their respective plane of assembly in order to free the front end of the munition body. Application: Steered or guided munitions such as those of the rocket or projectile type or missiles. | 10-10-2013 |
| 20130270391 | AIRCRAFT FUSELAGE DRAG REDUCTION BLIVET - An air vehicle fuselage adapted for transonic operation is disclosed. The fuselage has a body and a close-out. A lower surface of the body has a waterline value that varies along a fore-aft direction of the fuselage and is equal to a first waterline value at a forward end of the close-out and rise to a second waterline value at an aft end of the close-out. The lower surface has a drag-reduction blivet that includes a first region wherein the lower surface drops to a point comprising a third waterline value that is below the first waterline value and a first inward radius and then rises over a second region disposed aft of the first region wherein a second radius that is a minimum radius of the lower surface within the second region is greater than the first radius. | 10-17-2013 |
| 20130270392 | INTERFACE ARRANGEMENT FOR AIRCRAFT LIFTING SURFACE - Interface arrangement for aircraft lifting surface between a first component and a second component made of composite materials and having an aerodynamic contour, wherein the first component comprises a primary joggled area and the second component comprises a secondary joggled area, such that the first component is joined to the second component by means of a supplementary part which accommodates in the primary joggled area and in the secondary joggled area, the secondary part being designed to maintain continuity of aerodynamic contour at the interface arrangement and to fill the gap between the first component and the second component, so the maximum thickness of the supplementary part being the depth of the primary joggled area, the depth of the primary joggled area being lower than the depth needed to accommodate the second component on the first component. | 10-17-2013 |
| 20130320144 | AIRCRAFT LANDING GEAR - An aircraft ( | 12-05-2013 |
| 20140048653 | System and Method for Affixing Gateboxes to an Aircraft - A system for affixing a gatebox to an aircraft includes a first type of gatebox operable to release material from an aircraft, a second type of gatebox operable to release material from the aircraft, a frame coupled to the aircraft operable to receive a selected one of the first type of gatebox and the second type of gatebox; and a plurality of fastenings operable to secure the selected one of the first type of gatebox and the second type of gatebox to the frame. | 02-20-2014 |
| 20140131517 | AERODYNAMIC, BLUNT AFT BODY - An aerodynamic blunt aft body ( | 05-15-2014 |
| 20140332631 | AMORPHOUS METAL RIBLETS - An array of aerodynamic riblets is created by a plurality of high stiffness tips with a layer supporting the tips in predetermined spaced relation and adhering the tips to a vehicle surface. | 11-13-2014 |
| 20150048208 | Superconductive Hypersonic Liquefaction Nosecone - An apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements from the ambient air. The invention employs supercooling (through a combination of superconductivity and/or superemissivity) driven by the cryogenic power of liquid hydrogen and/or regenerative evaporation of liquid hydrogen and/or liquid nitrogen to drive isothermal compression and consequentially usurp the shock front in totality at Mach 1. The ensuing supercool/chilled air that is rendered as a consequence of supercooling may hence be compressed, regeneratively intercooled & flashed into liquid air. By means of extension liquid air may be rendered as a direct result of said supercooling throughout the hypersonic regime into space. Under conditions of optimality the incipient air stream may be compressed in accord with the stagnation pressure of the Mach number and liquefacted in one-step via the power of supercooling and isothermal compression | 02-19-2015 |
| 20150136909 | VIRTUAL AERODYNAMIC SURFACE SYSTEMS - A method of generating a pressure wave proximate an airflow surface and altering airflow to promote a localized lowering of skin friction over the airflow surface is described herein. A series of pressure waves may be configured to create a virtual riblet to control turbulent vortices in a boundary layer adjacent to the airflow surface creating a virtual riblet. The pressure waves may be configured to prevent disruption of the flow of air relative to at least one of a step or a gap associated with the airflow surface. The pressure wave generating system may be comprised of at least one of a thermoacoustic material, a piezoelectric material and a semiconductor material, and a microelectric circuit. | 05-21-2015 |
| 20150290915 | FILLING AND LEVELING METHODS AND APPARATUS FOR BUILDING TIGHT TOLERANCE SURFACES - Filling and leveling methods and apparatus for building tight tolerance surfaces are disclosed. An example method includes applying one or more of a tape or a sealant along an interior of a recess of a vehicle to move through a fluid. The example method includes leveling the one or more of the tape or the sealant to a first height at a first edge of the recess and a second height at a second edge of the recess to modify a fluid dynamic property of a fluid flow over the vehicle. | 10-15-2015 |
| 20150336659 | HYPERSONIC LAMINAR FLOW CONTROL - A novel passive control technique for laminar flow over air transportation vehicles and space reentry vehicles flying at high supersonic and hypersonic speeds is disclosed. The control of laminar flow can be achieved by applying an array of surface roughness elements in the region before the laminar-turbulent transition. For example, an array of two-dimensional rings, stripes, or closely packed three-dimensional isolated roughness elements may be used to stabilize the instability waves and delay transition. The roughness elements may have a height between 40% and 60% of the local boundary-layer thickness. The exact location, height, and spacing of surface roughness elements may be determined by a numerical simulation strategy based on the most unstable second mode, e.g. using known e | 11-26-2015 |
| 20150369576 | Apparatus and Methods for Hypersonic Nosecone - An apparatus and method for mitigating the shock front or reducing drag of a rocket or aerospace plane flying at hypersonic speeds by using a modified nose cone that incorporates a low temperature substance, such as liquid nitrogen, and where the nose cone simultaneously interacts with the ambient air to further supercool the nose cone during operation. | 12-24-2015 |
| 20160001888 | AFT PYLON FAIRING FOR AIRCRAFT - Aft fairings for aircraft pylons are disclosed. In one example, a fairing includes: two opposite side panels extending generally along a longitudinal direction of the fairing; a plurality of transverse ribs interconnecting the two opposite side panels; and a heat shield for exposure to a primary flow of an aircraft engine. The heat shield includes transversely opposed side end portions and a mid portion disposed between the transversely opposed side end portions. The heat shield is secured to the ribs via the mid portion of the heat shield. The transversely opposed side end portions are permitted to move outwardly from the mid portion due to thermal expansion of the heat shield. | 01-07-2016 |
| 20160114879 | Superconductive Hypersonic Liquefaction Nosecone - An apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements from the ambient air. The invention employs supercooling driven by the cryogenic power of liquid hydrogen and/or regenerative evaporation of liquid hydrogen and/or liquid nitrogen to drive isothermal compression and consequentially usurp the shock front in totality. | 04-28-2016 |
| 20160121996 | Spoiler for an Aircraft Bay - A method for managing an airflow of an aircraft. A spoiler is moved into the airflow passing a bay of the aircraft when the bay is open. The airflow moving relative to the bay is changed to form a desired airflow using louvers physically associated with a frame system in the spoiler. | 05-05-2016 |
| 20160137292 | AERODYNAMIC COMPONENT AND METHOD FOR PRODUCING AN AERODYNAMIC COMPONENT - An aerodynamic component which in particular is suitable for use in an aircraft includes an outer skin sheet having an inner surface and an outer surface and being provided with perforation openings allowing a flow of air therethrough. The outer surface of the outer skin sheet forms an aerodynamic surface of the aerodynamic component. The aerodynamic component further includes a sandwich panel which includes an outer layer facing the inner surface of the outer skin sheet, an inner layer facing away from the inner surface of the outer skin sheet and a foam core sandwiched between the outer layer and the inner layer. The sandwich panel is provided with connection openings extending through the sandwich panel between the outer layer and the inner layer and allowing a flow of air therethrough. | 05-19-2016 |
| 20160144950 | WING AERIAL REFUELING SYSTEM - An aircraft comprises a wing assembly, a pod, and a pylon attaching the pod to the wing assembly. The pylon has a swept pylon flap, which is configured to unload the pylon and pod during flight of the aircraft, and also to create downward flow that counters a vortex trailing the pod. | 05-26-2016 |
| 20160252334 | SUPERSONIC PROJECTILE NOSE CONES WITH FLAT TIPS | 09-01-2016 |
