Abstract: A method for assisting piloting beyond an altitude that can be reached with only the capabilities of a thermal power plant of a rotorcraft, by supplying power from an electrical power plant. After defining a take-off point of the rotorcraft and a target point, and their respective altitudes, a determination of a first maximum altitude that can be reached by the rotorcraft using only the thermal power plant is carried out according to a first altitude law. Then, an estimate of a second maximum altitude that can be reached by the rotorcraft using the thermal power plant and the electrical power plant jointly driving each rotor of the rotorcraft is made according to a second altitude law. If the second maximum altitude is higher than the altitude of the target point, the rotorcraft can fly to the target point.

Abstract: An apparatus and method for providing three-dimensional decoy having removeable or interchangeable body parts. The decoy includes an interchangeable head or support pole having a connecting system that quickly interlocks the head or pole to the decoy body. Further, the connecting system engages the head or support pole to the body with enough resistance that the decoy stays together in heavy winds and may be lifted by holding the head without disengaging from the body.

Abstract: A flow body for an aircraft includes a skin having a first flow surface, having a flow influencing section with at least one first layer, at least one separator layer, at least one third layer, and at least one base layer. The first layer includes lithiated carbon fibers embedded into a matrix to form a negative electrode. The third layer includes carbon fibers with an electrode active material coating to form a positive electrode. The separator layer includes a non-conductive material for electrically isolating the first layer and the third layer from each other. The flow influencing section is configured for selectively raising a region of the arrangement of first layer, separator layer and third layer from the base layer upon application of a voltage between the first and third layers to form a bump on the flow body.

Abstract: Using at least one mobile security camera to monitor multiple locations includes providing a plurality of landing platforms for the at least one mobile security camera, positioning the at least one mobile security camera at a particular one of the landing platforms in response to the particular one of the landing platforms being a preferred location of the at least one mobile security camera, and moving the at least one mobile security camera from a preferred location to follow a detected object. Using at least one mobile security camera to monitor multiple locations may also include returning the mobile security camera to the particular one of the landing platforms after the at least one mobile security camera follows the detected object. The at least one mobile security camera may perform static monitoring from the first one of the landing platforms and the second one of the landing platforms.

Abstract: This invention is directed toward an aerodynamically designed drone with a unique angle of propulsion. The drone uses airfoil design to move more efficiently through the air, and the aerodynamic design is optimized when the drone is tilted forward at various degrees of “tilt” to provide the most aerodynamic profile to the oncoming air. The invention contemplates single hull, double hull and triple hull designs, and is applicable to heaving lifting drones, drones use for photography and remote sensing, and racing drones.

Abstract: A wingless compact aircraft, with a limited footprint and no exposed high-speed moving parts. The aircraft can takeoff and land vertically, can fly at high-speed and even cruise on land and water in one of the preferred embodiments.

Abstract: A floor panel for an aircraft or spacecraft. The floor panel has a panel-like portion and an additional structure. A first side of the panel-like portion forms part of a floor surface in the aircraft or spacecraft. The additional structure is connected to the panel-like portion on a second side of the panel-like portion that is opposite the first side. The panel-like portion and the additional structure each comprise a matrix material formed by a thermoplastic material. Endless reinforcing fibers are embedded in the matrix material of the panel-like portion. Discontinuous reinforcing fibers are embedded in the matrix material of the additional structure. An aircraft or spacecraft may have a floor area which is formed by a planar arrangement of floor panels of this type. The method for producing a floor panel for an aircraft or spacecraft is provided.

Abstract: Engine bleed air power recovery systems and related methods are disclosed. An example power recovery system for an aircraft engine includes a power recovery turbine coupled to aa shaft-driven device. A bleed air valve coupled between the power recovery turbine and a bleed air source. A controller configured to operate the bleed air valve to allow bleed air to flow to the power recovery turbine when the aircraft engine operates in a predetermined mode of operation.

Abstract: An aircraft passenger seat construction capable of in-flight rocking motion and berthing, wherein rocking motion and berthing are mutually exclusive features. The seat construction includes a fixed frame including spaced frame members each having a support surface to be rocked on, a rocking frame including a seat pan and spaced rockers, the spaced rockers positioned to rock on the support surfaces, guides carried on the spaced rockers engaged to travel within guide slots of the spaced frame members, a backrest pivotally attached to the rocking frame, and a leg rest pivotally attached to the rocking frame. The rocking frame may rock back-and-forth in-flight or may be locked at any given position based on passenger preference. The seat construction is compatible with or without other seat adjustment mechanisms such as tracking, swivel, lie-flat and recline adjustment mechanisms.

Abstract: An unmanned aerial vehicle (UAV) for a remote oceanic environment includes a float system, at least one electric motor, and a seawater battery. The float system allows the UAV to maintain buoyancy on a body of water. The electric motor or motors produce the required lift for the UAV to achieve and maintain flight. The flight includes the UAV landing on the body of water and takeoff from the body of water. The seawater battery directly or indirectly powers the electric motor or motors using seawater from the body of water while the UAV is floating on the body of water.

Abstract: Heat exchangers, heat exchanger systems, and hypersonic vehicles are provided. For example, a heat exchanger is provided that comprises a first chamber for receipt of a flow of cool fluid and a second chamber for receipt of a flow of hot fluid. The heat exchanger further comprises a buffer fluid flowpath for circulation of a buffer fluid therethrough. The buffer fluid circulates within the buffer fluid flowpath disposed between the first chamber and the second chamber to transfer heat from the hot fluid to the cool fluid. In certain embodiments, a hypersonic vehicle comprises such a heat exchanger, and the cool fluid is cryogenic or near-cryogenic fuel of the hypersonic vehicle and the hot fluid is engine bleed air from a hypersonic propulsion engine of the vehicle.

Abstract: A bonded structure is described. The bonded structure includes an outer structure including a close tolerance hole associated with a first accuracy level. The bonded structure includes an interior structure comprising an oversized hole associated with a second accuracy level that is different from the first accuracy level. The bonded structure includes an elastomeric grommet disposed in the oversized hole. The bonded structure includes one or more spacers between the outer structure and the interior structure providing a space between the outer structure and the interior structure. The bonded structure includes a fastener positioned in the close tolerance hole and in the oversized hole. The bonded structure includes a bonding media disposed in the space between the outer structure and the interior structure via one or more channels of the fastener. The bonding media, elastomeric grommet, and oversized hole collectively position the interior structure relative to the outer structure.

Abstract: A structural system for lifting cells, constructed of modular, lightweight framing supporting thin, lightweight, single-ply or laminated, air-impermeable membranes, that maintain near constant-volume under low pressure for aerostatic lift in lighter-than-air aircraft; a system for controlling that aerostatic lift in a single or a plurality of such lifting cells, using electrically-powered vacuum pumps and valves; and a system for recovering electrical energy expended during ascent by using the inflow of air into the lifting cells during descent to generate electricity.

Abstract: A low drag surface is provided for a fluid washed object, the low drag surface comprising an aerodynamic surface comprising a cut-out region, and a continuously translatable surface comprising a surface portion. The surface portion is positioned in the cut-out region such that the aerodynamic surface and the surface portion form a fluidwash surface, and the surface portion is translatable relative to the aerodynamic surface.

Abstract: A static plate heating arrangement includes a faceplate including a port extending from an exterior surface of the faceplate to an interior surface of the faceplate, a fixed resistance heater in thermal communication with the interior surface and surrounding the port, and a self-regulating heater in thermal communication with the interior surface and surrounding the fixed resistance heater. The fixed resistance heater and the self-regulating heater are electrically connected in series.

Abstract: A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft has an airframe including first and second wings with first and second pylons coupled therebetween. A distributed thrust array is coupled to the airframe including a plurality of propulsion assemblies coupled to the first wing and a plurality of propulsion assemblies coupled to the second wing. A UAV carrier assembly is coupled between the first and second pylons. The UAV carrier assembly has a plurality of UAV stations each configured to selectively transport and release a UAV. A flight control system is configured to control each of the propulsion assemblies and launch each of the UAVs during flight.

Abstract: A rigid-flexible coupled unmanned aerial vehicle (UAV) morphing wing and an additive manufacturing method thereof are disclosed. A shape memory alloy (SMA) strip/wire for controlling the wing upward deformation and an SMA strip/wire for controlling the wing downward deformation are arranged alternately, and a plurality of reinforcing ribs are arranged at intervals on the SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation. The SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation are arranged on a flexible substrate, and are wrapped with an insulating covering. The SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation each are provided with an electric heating element.

Abstract: A hybrid electric powerplant can include an electric motor configured to convert electrical energy into kinetic energy to turn a propulsor, and a heat engine configured to convert a fuel into kinetic energy to turn the propulsor. The powerplant can include a firewall disposed around at least one of the electric motor or the heat engine to create an electric motor fire zone and a heat engine fire zone separate from the electric motor fire zone such that the electric motor is protected against a heat engine fire, and vice versa.

Abstract: A storage and release mechanism for aerial distribution and release of insects from an unmanned aerial vehicle, the release being aimed at controlling a wild insect population, the wild population having fluctuating local densities, the mechanism comprising a switch for switching between two or more different sustainable insect delivery rates for release of the insects. The method is particularly suitable for sterile male mosquitoes in programs to control wild mosquito populations.