Abstract: A deployable ottoman extension fills the gap between the ottoman and fully reclined oblique aircraft seat. The deployable ottoman extension can pivot out from the ottoman about a pivot point and/or slide out along a rail. Alternatively, the ottoman extension may be hinged to the ottoman to deploy by flipping down. The deployable ottoman extension may include deployable support features that extend to the aircraft floor when deployed.

Abstract: A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

Abstract: An airplane emergency escape drone is shown and described. The airplane emergency escape drone includes a life support system secured within a housing with a compressed air tank that controls the amount of oxygen from an oxygen tank and air from an air tank released into the housing. The airplane emergency escape drone also includes an inflatable floatation device secured to the housing. The airplane emergency escape drone also includes propellers having safety grates underneath the propellers. The airplane emergency escape drone also includes a CPU that is in connection with a video control system that includes a video input component and a signal transmitter.

Abstract: An aerial vehicle has a loading section whereon a payload and the like can be loaded. The aerial vehicle is capable of traveling at least forward and backward, is provided with lift generation sections, arm sections for holding the lift generation sections, a loading section disposed on the arm sections and positioned posterior to the center of gravity of the aerial vehicle, and a maintaining means for maintaining the aerial vehicle at least in the horizontal attitude, and the loading section has a first connection part for maintaining a loaded object at least in the horizontal attitude. On the basis of the above mentioned, the payload can be prevented from entering slipstream regions created by propellers, improving flight efficiency.

Abstract: A submersion system for a rotorcraft is described and includes a control module for controlling a depth to which the rotorcraft is submerged in a body of water; a compressed air chamber associated with the control module; and at least one flotation pod including a sealable opening on a top surface thereof and an opening on a bottom surface thereof. The control module selectively causes water to be taken into the at least one flotation pod to cause the submersion system to submerge in the body of water and selectively causes water to be evacuated from the at least one flotation pod to cause the submersion system to float in the body of water.

Abstract: An unmanned aerial vehicle (UAV) jettison apparatus. The UAV jettison apparatus may comprise a payload bay, fairing, ejector plate, and releasable latch. The payload bay may be mounted beneath an aircraft and may have an inner space and a top plate attached therewith. The fairing may substantially cover the inner space of the payload bay and may have an opening positioned directly below the top plate. The ejector plate, which may be spring-loaded, may substantially cover the opening and may be used to mount the UAV. The releasable latch, which may be disposed between the top plate and the ejector plate, may releasably lock and hold the UAV in a stowed position and, upon release, may allow the ejector plate to move into a launch position, such that the UAV is released and jettisoned from a larger aircraft.

Abstract: A lavatory enclosure for an aircraft, reconfigurable to accommodate a stretcher, includes a first wall, a second wall, a third wall, and a fourth wall. The lavatory enclosure has a doorway in the third wall and a door having a first side, a second side, an upper end, and a lower end, in the doorway. The door is operable between an opened position and a closed position. A reconfigurable wall element with a first edge and a second edge is disposed in the second wall. The reconfigurable wall element has a hinge along the first edge permitting the reconfigurable wall element to pivot between a closed position, where the reconfigurable element is flush with the second wall, and an opened position, where the second edge of the reconfigurable wall element is pivoted so that the second edge is interior to the lavatory enclosure.

Abstract: A method of additively manufacturing a spacecraft panel includes printing a first skin and a second skin, spaced apart from the first skin. The method further includes printing a first truss structure connecting the first skin to the second skin.

Abstract: A maritime vehicle includes a surface for contacting a fluid medium through which the maritime vehicle is propelled. The maritime vehicle also includes an array of transducers and a controller. The transducers in the array are arranged across the maritime vehicle's surface for generating pressure waves in the fluid medium. Each transducer in the array is arranged to vibrate for generating a respective pressure wave, which propagates away from the surface in the fluid medium. The controller vibrates the transducers in the array so that the pressure waves control the drag of the maritime vehicle from the fluid medium.

Abstract: A reconfigurable hybrid Vertical Takeoff and Landing (VTOL) vehicle includes a turntable bearing coupling a conventional wing to a fuselage. The fuselage, designed to couple to and release a cargo pod from its undercarriage, is configured to accept a high wing juncture such that the wing can rotate from a flight configuration to a transport configuration. The transport configuration aligns the wing with the fuselage sufficient to enable the hybrid VTOL vehicle to fit within a standard intermodal container or transport aircraft.

Abstract: A system for optimizing a low-thrust trajectory of a spacecraft trajectory for orbital transfer includes an interface to receive data, a memory to store scheduled geostationary transfer orbit (GTO) data and scheduled geostationary Earth orbit (GEO) data and computer-executable programs, and a processor.

Abstract: Various embodiments of a variable geometry quadrotor with a compliant frame are disclosed, which adapts to tight spaces and obstacles by way of passive rotation of its arms.

Abstract: Compliant mounting systems, devices, and methods for mounting a vehicle engine to a vehicle structure or base include a top mount, a lower mount, a center trunnion mount, and an aft mount which are configured to react forces transmitted by the engine to the vehicle structure. Metallic and elastomeric elements can provide vibrational and force isolation characteristics. Stops (e.g., snubbing elements) allow for a specific range of motion before internal mount structures contact each other to act as a conventional hard mount. Fluid elements and compressible gas-filled spaces/bladders may be incorporated to provide fluid damping behaviors to complement the metallic and elastomeric elements.

Abstract: A floor mounted aircraft seat seal frame includes a frame, displacing elements connecting the frame to the posterior of the seat, and fabric tensioning elements that keep a gap covering fabric connected to the posterior surface of the seat in tension around the frame. The frame displacing elements, which may be leaf springs, coil springs, or manually adjustable element, allow the frame to conform to a wall behind the seat, regardless of the tapering of the wall.

Abstract: A latch assembly for a decompression panel in an aircraft includes a base and a swing arm hinged to the base and pivotable relative to the base about a hinge axis between a latched position and an unlatched position. A load pin fixed to the swing arm has a pin axis a fixed distance from the hinge axis. A spring secured to the base is positioned to exert a spring force against the swing arm when the swing arm pivots from the latched position to the unlatched position. A bracket securable to the decompression panel defines a slot retaining the load pin when the swing arm is in the latched position. The load pin is movable in the slot under relative motion of the bracket and the base with the swing arm in the latched position, and exits the slot when the swing arm pivots to the unlatched position.

Abstract: Deployment system for adjusting a leading edge high-lift device, in particular a slat, between a retracted position, in which, in use, the high-lift device is retracted with respect to an airfoil, and at least one deployed position, in which, in use, the high-lift device is deployed with respect to the airfoil, comprising at least one actuation unit that is configured to actuate the high-lift device between the retracted position and the at least one deployed position, at least one guidance unit that is configured to guide the high-lift device during adjustment between the retracted position and the at least one deployed position along an adjustment path, wherein the guidance unit is independent from the actuation unit.

Abstract: A balloon system, preferably including a balloon and a payload. A balloon, preferably including a plurality of gores, a plurality of load members, and an apex fitting. A method of balloon system operation, preferably including deflating a balloon, and optionally including operating the balloon system in flight and/or landing the balloon system.

Abstract: A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.

Abstract: A payload retrieval apparatus is provided including a stand or base, wherein the base or stand has an upper end and a lower end, a first sloped surface positioned over the upper end of the stand or base, a second sloped surface positioned over the upper end of the stand or base and adjacent the first sloped surface, a tether slot positioned in a channel having a first end and a second end, the channel positioned under or near the first sloped surface, and a payload holder positioned at the second end of the channel, wherein the payload holder is adapted to secure a payload.

Abstract: An armrest assembly for a passenger seat may include an armrest and an attendant step assembly. The armrest may include a top side and a bottom side, and the attendant step assembly may be connected to the bottom of the armrest. The attendant step assembly is movable between a stowed position and a deployed position relative to the bottom side of the armrest.