Abstract: A fuel system for an aircraft can include one or more airframe fuel lines configured to transfer fuel from one or more fuel tanks to an engine, one or more engine fuel pumps in fluid communication with the one or more airframe fuel lines and configured to pressurize fuel from a main stage boost pressure to a combustor pressure to be injected into a combustor of an engine, one or more airframe fuel pumps configured to pressurize fuel within the one or more airframe fuel lines to the main stage boost pressure used by the engine fuel pump. For example, the main stage boost pressure can be about 250 psi.

Abstract: In an example embodiment, an attitude, orbit, and de-orbit control system (AODCS) for a satellite is provided. In an example embodiment, the AODCS system comprises one or more selectively retractable booms. The one or more selectively retractable booms are collectively configured to provide a selectively adjustable drag during de-orbiting of a satellite over a predefined de-orbiting time.

Abstract: A T-divider secures meal carts against lateral movement, and is at least partially deflectable to allow the meal carts to be removed from a restricted environment. The T-divider is secured in linear orientation via a latch with one or more indicators; one indicator indicates if the latch is locked; another indicator indicates if the T-divider is secured. The movement of the T-divider is defined by a track. One or more stops on the track define a linear, secured orientation and a fully deflected orientation.

Abstract: A rotor assembly for use in an aircraft comprising has a rotor hub, a spinner structure comprising a spinner opening, and a rotor blade received through the spinner opening. The rotor blade has a rotor root located proximate to the rotor hub. The rotor assembly also has a motive fairing face that at least partially rests along the rotor hub.

Abstract: A rotor blade for a rotary wing aircraft includes a rotor hub including a first flex-beam attachment member and a flex-beam assembly. The flex-beam assembly includes a flex-beam support member having an attachment end and a wrapping end. A first flex-beam includes a first end, a second end and an intermediate portion. The first end of the first flex-beam is connected at the first flex-beam attachment member and the second end of the first flex-beam being connected to the attachment end of the flex-beam support member. A second flex-beam includes first end portion, a second end portion and an intermediate section. The first end portion of the second flex-beam is connected at the first flex-beam attachment member, the second end portion of the second flex-beam being connected at the second flex-beam attachment member and the intermediate section extending about the wrapping end of the flex-beam support member.

Abstract: A modular subfloor system comprises first longitudinal structural frames, lateral regions, and a modular tank system that is connected to the first longitudinal structural frames. The modular tank system comprises a bottom shell, an upper panel, second longitudinal structural frames arranged between the bottom shell and the upper panel and transversal structural frames that are arranged between the bottom shell and the upper panel. The transversal structural frames and the second longitudinal structural frames form compartments. The modular tank system further comprises tank bladders arranged in at least some of the compartments and sealing elements that seal the upper panel, the bottom shell, and the at least some of the compartments of the modular tank system.

Abstract: Provided is a high efficiency long range drone, and more particularly, a high efficiency long range drone capable of increasing flight time and efficiently using power during long range cruising flight by selectively using the power among an engine generator and a battery and applying an auxiliary wing.

Abstract: An aircraft includes first and second zones, and a sealing system, interposed between a doorframe and a door providing access to the second zone, including: a peripheral seal secured to the door, a stop secured to the doorframe, and including a body in the form of at least one plate which extends around the perimeter of the doorframe, parallel to the door when the door is in the closed position, a peripheral groove positioned on the stop in such a way that the peripheral seal closes off the peripheral groove around the perimeter of the opening when the door is in the closed position, and at least one passage configured to cause the peripheral groove and the first zone to communicate.

Abstract: A spar for a wing includes a monolithic structure and a strut. The monolithic structure includes an upper chord, a lower chord, and a web positioned between the upper chord and the lower chord. The strut, distinct and separate from the monolithic structure, is coupled to the monolithic structure between the upper chord and the lower chord and extends across the web.

Abstract: A hybrid power tri-propeller helicopter apparatus for efficient and quiet flying includes a helicopter body, a cockpit portion, an engine portion, a tail boom portion, a gas motor, a generator, a battery pack, and an electric nose motor. A nose propeller and a lift propeller support are coupled to the helicopter body. A pair of electric lift motors is coupled to the lift propeller support and is in operational communication with the battery pack. A pair of lift propellers is coupled to the pair of lift motors. A tail fin and a pair of horizontal rear stabilizer fins are coupled to the tail boom portion. A pair of front stabilizer fins is coupled to the cockpit portion. A plurality of controls is coupled to the cockpit portion and is in operational communication with the nose motor, the pair of lift motors, and the pair of rear stabilizer fins.

Abstract: A flap assembly for a fixed wing aircraft, comprising first and second flap portions, a compartments in the flap portions enclosing rechargeable batteries, motor controllers and electric motors, vertically-oriented slots in the first flap portion with propellers operable through a sidewall of the slot, such that the propeller in operation extends both over and under the top and bottom walls of the flap portion. With the flap assembly retracted in the wing the propeller is entirely enclosed in the length of the slot, and wherein the flap assembly is extended from the edge of the wing, enhancing area and curvature of the wing, increasing lift on the wing, exposing the slot, and with the slot exposed the motor is started spinning the propeller, providing increased airflow over the flap assembly, further increasing lift on the wing.

Abstract: A passenger door arrangement for an aircraft segment, which arrangement comprises a passenger door, which is configured to assume a raised state and a lowered state, and a “girt bar,” for arming and disarming an escape slide, the girt bar not altering its position relative to the passenger door in the transition from disarming to arming, when the passenger door is in the lowered state. Additionally an aircraft segment, which comprises the passenger door portion and a fuselage portion, an external engagement arrangement being fixed to the fuselage portion.

Abstract: A fuel system for a rotorcraft is provided. The fuel system comprises a housing, a fuel bladder located within the housing, a first fuel reservoir, and a number of pressure relief valves. The first fuel reservoir is in fluid communication with the fuel bladder and stowed within the housing. The number of pressure relief valves are configured to divert fuel from the fuel bladder into the first fuel reservoir at a predetermined pressure such that the first fuel reservoir expands to reduce forces on the housing during a crash event.

Abstract: Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence of a wing of an aircraft. The fence includes a base that is coupled to the wing and a panel that is movable relative to the base and the wing between a stowed position in which the panel extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the panel is in the deployed position. The panel is configured to move from the deployed position to the stowed position in response to an aerodynamic force exerted on the panel.

Abstract: To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

Abstract: Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the fence is in the deployed position. The fence is configured to move from the deployed position to the stowed position in response to an aerodynamic force exerted on the panel.

Abstract: Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the fence is in the deployed position. The fence is configured to move from the stowed position to the deployed position in response to an aerodynamic force exerted on a deployment vane of the fence.

Abstract: Automated deployable fences for aircraft wings are described. An example apparatus includes a fence, a latching actuator, and a biasing actuator. The fence is coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel impedes a spanwise airflow along the wing when the fence is in the deployed position. The latching actuator is movable between a first position in which the latching actuator maintains the fence in the stowed position, and a second position in which the latching actuator releases the fence from the stowed position. The latching actuator moves from the first position to the second position in response to a control signal received at the latching actuator.

Abstract: An element including a leading edge forming a box delimited by a skin forming a lower surface and an upper surface and pierced with holes, in which the skin includes an inner wall and an outer wall that are electrically conductive and an electrically insulating intermediate wall, a pump for expelling or injecting air from or into the box. Each hole is equipped with an anti-clogging system including a conductive base, a needle made of piezoelectric material, one end of which is secured to the base, an electrical generator generating an electrical current in the needle, in which the form of the needle is such that a space is created between the needle and the edges of the hole, and in which the base has a recess in the extension of the space. Such an installation makes it possible to eliminate the residues which are lodged in the holes.

Abstract: A wing comprising a fixed main part and a leading edge slat with upper and lower surface rear edges. The wing main part has an upper surface wall, which extends downstream and in alignment with the upper surface rear edge, and a lower surface wall, which extends downstream and in alignment with the lower surface rear edge. The wing has an upper surface gap between the end of the upper surface rear edge and the end of the upper surface wall and a lower surface gap between the end of the lower surface rear edge and the end of the lower surface wall. The wing has an upper surface channel downstream of the upper surface gap and a lower surface channel downstream of the lower surface gap. The wing comprises a suction system connected to each channel and arranged to suck the air contained in the channel.