Abstract: A vehicle surface includes a set of retroreflectors configured to reflect, at least in part, incident hostile light towards a source of the incident hostile light.

Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.

Abstract: Various implementations described herein are directed to an aircraft. The aircraft includes an airframe; and a windshield system having a transparent canopy coupled to the airframe and a transparent inner panel having a portion thereof disposed within the transparent canopy and coupled to the airframe and to at least a processor.

Abstract: A system for initiating a canopy release signal for a canopy of an aircraft includes a first striker secured to the canopy, and a first initiator assembly secured to a fuselage of the aircraft. The first initiator assembly has a protrusion. The first striker is configured to be rotated against the protrusion of the first initiator assembly. The canopy release signal is output in response to the first striker rotating against the protrusion of the first initiator assembly.

Abstract: An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.

Abstract: A radar-absorbing material projectile system including a projectile with an outer layer of radar-absorbing material (RAM). A carrier or armature is disposed around the projectile, protecting the layer of RAM during the firing sequence. In some embodiments the carrier is a discarding carrier which falls away after firing, rendering the projectile low-observable with regard to radar detection due to the layer of RAM.

Abstract: A canopy for an aircraft includes a pivot assembly including a first hinge and a second hinge opposite from the first hinge. The first hinge includes a first pivot slot having a first length. The first pivot slot is configured to retain a first aft pin of a fuselage of the aircraft. The second hinge includes a second pivot slot having a second length. The second pivot slot is configured to retain a second aft pin of the fuselage of the aircraft. The first length differs from the second length.

Abstract: The present invention is directed to multiple arrangements of a self-disengaging pitot tube cover, which can be triggered by a plurality of different environmental conditions while the cover admits to a plurality of different latching mechanisms and opening configurations to guarantee the expeditious, automatic removal of the pitot tube cover while avoiding damage or contamination of the pitot tube itself.

Abstract: An inflatable pod system on an aircraft includes an inflatable pod including a nozzle to receive air for inflation of the inflatable pod, and a hose assembly including a first end having an adaptor fitting that is configured to press fit with an air duct nozzle of an air duct of the aircraft and a second end having an adaptor configured to couple to the nozzle. In an example, the hose assembly delivers bleed air from the air duct, as provided by an environmental control system (ECS) of the aircraft, to the inflatable pod to inflate the inflatable pod. In another example, an air duct assembly line couples the ECS with the inflatable pod, and a control system triggers inflation via the air duct assembly line based on receipt of an electronic inflation signal.

Abstract: A head and neck support and protection device includes an arm that is pivotably mounted, at a first end, to a support and has at a second end a slidably-mounted element connected to a helmet clip. The helmet clip engages a helmet pin. A resistance block transfers energy into a vehicle chassis when the arm hits the resistance block. The slidably-mounted element slides out of the arm, in a controlled manner, when conditions indicating a crash have been met.

Abstract: A windshield for an aircraft cockpit is provided which includes a glazed windshield part which has a single curvature corresponding to a portion of the envelope of a cone extending between a lower plane and an upper plane which intersect an axis of the cone. The single curvature of the glazed part of the windshield enables the glazed part to be produced more easily, for example by rolling or by hydroforming. It also makes it possible to create configurations for a cockpit for two pilots, a single pilot or even no pilot, on the basis of a single aerodynamic shape of the fuselage of the aircraft by only adapting the structure of the windshield. Also provided are a windshield frame for such a windshield, a windshield assembly including such a windshield frame and such a windshield, and an aircraft equipped with such a windshield.

Abstract: A seat for a vehicle includes a seatback having a seat frame. The seat includes an airbag supported on a vehicle-rearward and vehicle-outboard corner of the seat frame. The airbag is inflatable to an inflated position. The airbag includes a cross-vehicle chamber inflatable in a vehicle-inboard direction behind the seatback and a vehicle-outboard chamber inflatable in a vehicle-rearward direction.

Abstract: An electrically powered STOL aircraft having dedicated motors energized to deploy movable landing gear driven to propel short takeoffs and to actively rotate downwardly to engage the runway surface as the aircraft approaches touchdown on landing. The front and rear landing gear, or both, may be powered and actuated in the landing process with braking to shorten the landing distance, each driven landing gear wheel having a dedicated electric motor and coaxial brake. The landing gear modules are configured and controllable to differentially deploy downwardly so as to enable countersteering during taxi maneuvers and turns.

Abstract: Aircraft canopy jettison systems, apparatus, and methods are described herein. An example aircraft includes a forward fuselage defining a cockpit, a seat in the cockpit, a pivot pin coupled to the forward fuselage, and a canopy removably coupled to the forward fuselage over the cockpit. The canopy includes a frame having a hinge portion. The hinge portion includes a cam. The cam is dimensioned such that when the canopy is jettisoned while the aircraft is at zero altitude and zero airspeed, a travel path of the hinge portion does not intersect a travel path of the seat when the seat is ejected while the aircraft is at zero altitude and zero airspeed.

Abstract: A vehicle seat includes a seat bottom having a forward-facing surface relative to the vehicle seat and an airbag mounted to the seat bottom. The airbag includes an inflator mounted to the seat bottom and an airbag cushion including a portion positioned adjacent the forward-facing surface of the seat bottom.

Abstract: A system for increasing passenger safety within an airplane (10) includes a forward seat (16) having a back surface (17) that faces an occupant seat (14). A tray table holder (22) is secured to or formed integrally with the back of the forward seat (16). A tray table (20) is rotatably connected to the tray table holder via a hinge (40) and is rotatable relative to the tray table holder. The tray table defines a cavity (32) inside the tray table. An airbag (54) is within the cavity. An inlet device (42) is coupled to the airbag and is rotatable about the hinge (40) such that the inflator inlet can rotate as the tray table rotates relative to the tray table holder. An inflator (52) is connected to the inlet device and is configured to deliver gas to the airbag through the inflator inlet.

Abstract: An aircraft fuselage includes: at least one lower part, at least one upper part, structural connections connecting the lower part and the upper part in joining zones, in each joining zone, at least one space between the lower and upper parts and the structural connections, and a transparent wall for closing off each space.

Abstract: An arm restraint assembly configured to pierce a canopy in response to expulsion of an ejection seat from a cockpit may comprise a primary arm configured to pivot relative to the ejection seat. A canopy piercer may be coupled to the primary arm. The primary arm may be configured to rotate to a fully-deployed position while located within the cockpit. An apex of the canopy piercer may be oriented toward the canopy, when the primary arm is in the fully-deployed position.

Abstract: An aircraft fuel system including at least one fuel tank, a source of inerting gas, an inlet for introducing the inerting gas into the at least one fuel tank, and a vent system arranged to allow the inward and outward venting of air from the fuel tank. In embodiments, the vent system includes a vent, an inward vent pressure valve disposed between the vent and the at least one fuel tank and configured to enable the at least one fuel tank to increase by a predetermined pressure over ambient air pressure, and an outward vent pressure valve disposed between the at least one fuel tank and the vent and configured to enable the at least one fuel tank to decrease by a predetermined pressure below ambient air pressure.

Abstract: A method of repairing damage to a composite material having a composite substrate and at least one layer of shielding material includes: a) removing damage to the at least one layer of shielding material by creating a hole in the at least one layer of shielding material; b) applying a patch of shielding material in the region of the hole via a resin, wherein a ratio of a resin weight to a weight of the patch of shielding material lies in a range between about 0.45-0.55; and c) curing the resin, wherein an absorptive, consumable material is positioned in contact with the resin during at least a portion of the curing.

Abstract: A decompression panel assembly for use in an aircraft includes a body panel having an opening defined therein and a cover panel positioned within the opening and spaced from the body panel. The decompression panel assembly also includes an annular spacer panel positioned outboard from the cover panel and the body panel. The spacer panel is spaced from the cover panel to define a first annular flow path between the cover panel and the spacer panel, and the spacer panel is spaced from the body panel to define a second annular flow path between the body panel and the spacer panel.

Abstract: A panel door system has at least two support tracks and at least two panels hanging from the at least two support tracks. The at least two support tracks are mounted to a support structure such that each support track is offset from a previous support track both horizontally and vertically. The least two panels are hung using hanging mechanism such that each panel is hung on a different support track. The at least two panels create a door. The at least two panels are movable along the at least two support tracks in a first direction to open the door and in a second direction to close the door. The at least two panels stack horizontally with each other when the door is in the open position.

Abstract: Apparatuses for controlling gas flow are important components for delivering process gases for semiconductor fabrication. In one embodiment, an apparatus for controlling gas flow is disclosed, the apparatus delivering two gas flows at a known ratio. Specifically, the apparatus has first and second on/off valves and first and second flow restrictors. The first and second on/off valves may be altered between an open state and a closed state. When both the first and second on/off valves are in an open state, first and second gas flows are delivered to first and second outlets. The first and second gas flows are provided at a known ratio to one another, this ratio determined by the ratio of the resistance to flow of the first and second flow restrictors.

Abstract: Disclosed are front entry cabs, and power machines with front entry cabs, having a door that is moveable between opened and closed positions. In the opened position, the door is positioned within an operator compartment of the cab above the operator seat and below a top of the cab. A linkage system defines the travel path of the door between closed and opened positions. The linkage system is configured to minimize interference with operator visibility.

Abstract: A system includes a seat. The system includes an airbag supported by the seat. The airbag is inflatable to an inflated position. The airbag includes an inflation chamber and a panel adjacent to the inflation chamber defining a concave impact surface in the inflated position. The system includes a tether having a first end attached to a side of the airbag and a second end attached to the panel. The inflation chamber is beneath the concave impact surface in the inflated position.

Abstract: The forward firing fragmentation (FFF) munition includes a body, a flight system carried by the body and configured to maneuver the munition in flight, and a warhead carried by the body and including an explosive configured to detonate and expel fragments in a pattern. A near field barrier (near field barrier), such as the guidance system, is carried by the body in front of the warhead and communicatively coupled via a communication link to the flight system. A fragmentation adjustment system is configured to physically displace the near field barrier relative to the warhead while maintaining the communication link between the near field barrier and the flight system until detonation of the explosive.

Abstract: A motor vehicle (10) having a passenger compartment (12) and a front compartment (13) arranged in the direction of a longitudinal axis (X) in front of the passenger compartment (12) is provided. Here, the passenger compartment (12) is surrounded by a body (14) comprising a slope (16). In the front compartment (13), an auxiliary frame (17) is arranged. As claimed in the disclosure, a spacing (22) is formed between the auxiliary frame (17) and the slope (16) in the direction of the longitudinal axis (X) and a spacer piece (19) is arranged in this spacing.

Abstract: Methods for producing a flexible, fibrous ablator thermal protection material, for use in association with a space vehicle that passes through an atmosphere in which severe heating is experienced. A phenolic resin and/or a silicone resin can be used. The elastic modulus of the resulting material is low, in a preferred range of about 200-5000 kPa, and can be controlled by choice of a curing temperature and/or a time interval length for curing.

Abstract: A fire seals system positioned in a corner of a region of attachment between a rear engine mount and a pylon and comprising a metal shoe comprising a fitting comprising two first vanes forming an L fixed in the corner and a lower second vane between the lower edges of the two first vanes and an upper second vane between the upper edges of the two first vanes, and a flexible tongue having a fixed upstream end and a free downstream end in which an intermediate part of the tongue is arranged between the lower second vane and the upper second vane, and a longilinear seal attached to a thrust reverser cowl with one end of the longilinear seal bearing against the tongue. Such a fire seals system makes it possible to limit the spread of flames and to absorb movements of the nacelle.

Abstract: The present disclosure relates to an aircraft comprising a passenger module, and also a method of protecting a passenger on an aircraft. The passenger module is configured to be ejected through a skin of the aircraft in response to an ejection command. The ejection command may be given in response to a fatal condition to the aircraft being detected or manually indicated.

Abstract: A window or door system includes a window or door panel, a sidewall, and a frame bolted to the sidewall. In some arrangements, the frame is inverse U-shaped or O-shaped and includes a first channel for receiving the window or door panel. A trim member secured to the frame and extending across the U- or O-shape includes a second channel for receiving the window or door panel. A connector may extend through the trim member and the window or door panel across the second channel. The structure is configured to pass test requirements in ISO 8084, Machinery for Forestry—Operator Protective Structures.

Abstract: Systems and methods are provided for inflatable air pads for aircraft. One embodiment is an apparatus that includes an air pad affixed to a mount within an interior of an aircraft. The air pad includes a front face, a bladder that is inflatable within the air pad, and sides that constrain the front face of the air pad to extend a uniform distance outward from the mount when the bladder is inflated. The apparatus also includes an inflator that is coupled with the air pad and is configured to inflate the bladder from an undeployed volume to a deployed volume.

Abstract: A cyclic stick for transmitting control commands to blades of a rotorcraft via at least one transmission member, including a grip configured for engagement with a pilot's hand, a control arm and at least one locking mechanism. The control arm has a bottom end configured for connection to the transmission member(s) and for rotational connection to a base support structure, and a top end pivotally connected to the grip. The control arm includes first and second arm portions pivotally connected to each other, the first arm portion defining the bottom end, the second arm portion defining the top end. The locking mechanism(s) selectively prevent a relative pivoting motion between the first and second arm portions and a relative pivoting motion between the second arm portion and the grip. A method of adjusting a position of a grip of a cyclic stick in a rotorcraft cabin is also discussed.

Abstract: An example method includes: forming a conductive layer on at least a portion of a surface of a substrate, where the substrate comprises a composite material of an aerodynamic structure, and where the conductive layer is configured to provide a conductive path to conduct an electric current generated by a lightning strike to an electrically-grounded location; depositing an insulating layer on the conductive layer; removing one or more portions of the insulating layer to form respective gaps in the insulating layer and expose corresponding one or more portions of the conductive layer; and forming a resistive-heater layer on the insulating layer such that the resistive-heater layer fills the respective gaps in the insulating layer and contacts the corresponding one or more portions of the conductive layer, such that when electric power is provided to the conductive layer, the electric power is communicated to the resistive-heater layer thereby generating heat therefrom.

Abstract: An aircraft assembly may have a drag-inducing discontinuity 112. A seal assembly 101 includes a seal body 110 arranged to fair and/or seal the discontinuity 112; and a sealed chamber 114, wherein the sealed chamber 114 being pressurised such that in response to changes in the ambient pressure relative to the internal pressure of the chamber 114 the sealed chamber 114 alters the behaviour of the seal body 110.

Abstract: An apparatus comprising a chassis, a compartment and a safety system. The chassis may comprise a chassis base, curved rear chassis pillars and inclined front chassis pillars. The compartment may comprise a compartment base and curved rear compartment pillars. The safety system may be configured to (a) receive a signal and (b) activate a safety measure in response to the signal. The chassis supports the compartment. The compartment provides seating for occupants of a vehicle. The signal indicates an amount of force. The safety measure comprises (a) lifting a front of the compartment from the chassis, (b) rotating the curved rear compartment pillars along the curved rear chassis pillars and (c) absorbing the force with the chassis base while the compartment is lifted.

Abstract: A thermal protection system (TPS) for a space vehicle that undergoes partial or full ablation when the TPS is exposed to severe heating during entry into a planetary atmosphere. A first layer includes at least one of carbon, phenolic, silica, alumina and another oxide, low thermal conductivity fibers and yarns connecting two or more first layer sub-layers, is recession-resistant and has reduced porosity. A second layer has a smaller fiber fraction, reduced thermal conductivity and reduced density, and serves as a thermal insulator. The first layer may have partial or full insertion of a resin, or may have a surface densified, recession-resistant sub-layer. Values of a first subset of as many as eight environmental parameters can be used to characterize the space vehicle mission. A second subset of TPS parameters for the system is evaluated to identify whether an ablator system with these TPS values can survive the conditions associated with the first subset of environmental parameters.

Abstract: A structure for anti-adhesion of high-temperature air according to the present invention includes: a high-temperature air duct that is provided in an accessory of an aircraft and allows high-temperature air likely to be higher than a specified temperature to flow through the high-temperature air duct; an exhaust port that discharges a flow of the high-temperature air led through the high-temperature air duct, to an outside of the airframe; and a low-temperature air supplying part that supplies a flow of low-temperature air lower in temperature than the high-temperature air discharged to the outside of the airframe, to an airframe surface. The low-temperature air supplying part is configured to form an air layer made of a flow of low-temperature air between the high-temperature air that is bent toward the airframe surface in flight of the aircraft, and the an airframe surface.

Abstract: A blanket assembly for use in at least one bay and with at least one frame member of an aircraft, the assembly including an insulation blanket. The insulation blanket includes a bay section sized and shaped to fit within the bay and of sufficient thickness to provide insulation to the bay, a return section disposed on a first side of the bay section; and a cap section disposed on a second side of the bay section, opposite the first side. The cap section is sized and shaped to at least partially cover the frame member when the cap section is wrapped around the frame member, the cap section being of sufficient thickness to provide insulation to the frame member. The bay section, the return section, and the cap section are of unitary construction.

Abstract: A method for preparing a flexible low-density thermal protection material, the method comprising providing a flexible substrate and a pyrolizable material impregnated therein. The thermal protection material remains flexible after impregnation and continues to remain flexible when the pyrolizable material is fully pyrolized.

Abstract: A modular armor system configured to be readily attached and detached from a frame surrounding a window in a vehicle or other structure, such as a building. The modular armor system may be configured to provide any desired ballistics protection rating. In one embodiment, the modular armor system includes a ballistics-grade armor panel having an outer strike face and an inner surface opposite the outer strike face. The modular armor system also includes a fastener coupled to the ballistics-grade armor panel. The fastener is configured to detachably couple the ballistics-grade armor panel to the frame surrounding the window in the vehicle or other structure.

Abstract: Airfoil blades are disclosed having a coating thereon that includes a polyurethane, a polysiloxane, and a linking agent that promotes a connection between the polyurethane and the polysiloxane.

Abstract: An aircraft window includes: a window body including window panels, and an electromagnetic shield layer laminated on the window panels; a window frame that is made of a conductive material, and that surrounds the window body; a rubber-based gasket provided with conductivity, the gasket being at least partially held between the window body and the window frame; and a conductive layer that is located between the window body and the gasket, and that brings the electromagnetic shield layer and the gasket into conduction with each other. The window frame includes a holding section that holds the window body. At least a part of the conductive layer extends to a portion of the window body facing an extending part of the holding section. Moreover, the conductive layer extends about an entire perimeter of the window body, and extends only partially along an interface between the window body and interposition member.

Abstract: An inertial particle separator includes a body with an outer wall, an inlet, an outlet, an inner nozzle, a settling chamber, a serpentine channel, and a filter element. The inlet is disposed on an upstream end of the body. The outlet is disposed on a downstream end of the body. The inner nozzle is disposed radially inward from the outer wall and forms a primary flow passage. The settling chamber is disposed in the body and extends between the outer wall and the inner nozzle. The settling chamber forms a secondary flow passage and is fluidly connected to the inlet and the outlet. The serpentine channel fluidly connects fluidly connects the inlet and the settling chamber and is disposed radially between the outer wall of the body and the inner nozzle. The filter element is disposed in the settling chamber.

Abstract: An integrated knee bolster device for a vehicle is configured to restrict the depth of penetration of the knees of a seat occupant which strike a lower crash pad panel when a vehicle collision occurs, thus minimizing injury to the seat occupant, and enhancing safety performance for the seat occupant.

Abstract: This invention relates to a canopy locking and releasing apparatus for mounting a canopy to the fuselage of a vehicle. The canopy locking and releasing apparatus is comprised of several mechanisms. These include internal canopy locking and releasing mechanism, the external (Type A, B, or C) canopy locking and releasing mechanisms, a hinge plate and base mechanism, a hinge retaining pin, and a fuselage locking and releasing device for the hinge base. The apparatus is mounted on the sides of a canopy and attached to the cockpit of a vehicle. This apparatus allows for quick and easy opening of the canopy for routine or emergent access and driver entry or egress. An unique advantage of the canopy side mount locking and releasing hinge mechanism for vehicles is that the cockpit is easily accessible from either side of the vehicle, from the inside and outside of the vehicle, or if necessary, from both sides of the vehicle at once.

Abstract: A HMD system including a visor mounted on a head of a user. The visor includes adjustable light transmission layer activated by activation radiation of at least a visible activation waveband and an Ultra Violet (UV) activation waveband. The visor defines a Line Of sight (LOS) projecting from a point on the visor and further defines a Field Of View (FOV) projecting from at least a section of the visor that surrounds the point on the visor. The visor is configured to admit an outside scene image. The HMD system further includes a luminosity sensor configured to detect luminosity within the FOV and a UV activation radiation source configured to selectively irradiate at least a portion of the visor with activation UV light included in the UV activation waveband according to luminosity detected by the luminosity sensor, thereby activating the adjustable light transmission layer.

Abstract: An aircraft with a fuselage, wings, horizontal stabilizers and a vertical stabilizer, wherein on a front portion of the vertical stabilizer an elongated one-piece nose element is mounted which forms lateral air guide surfaces. To the front end of the nose element a perforated metal plate nose member is attached. The front end of the nose element being closed and between this closed front end and the nose member an elongated air channel is formed.

Abstract: A panel assembly that includes a front skin having a front surface, a back surface and at least one crush section portion, a core assembly that includes first, second, third, fourth and fifth layers laminated together, and at least a first crush section. The first, second, third, fourth and fifth layers each include a front surface, a back surface and at least one crush section portion. The front surface of the first layer of the core assembly includes a plurality of scores defined therein. The second layer includes a plurality of elongated voids defined therein and the fourth layer includes a plurality of elongated voids defined therein.

Abstract: The present disclosure relates to the active initiation of incident energy-dissipating material from a structure surface coating as a counter measure response for the protection of a structure surface. The active initiation is triggered at a predetermined area or areas on a targeted structure surface in response to incident directed energy sensed on a target surface.