Abstract: A heated leading-edge structure for an aircraft includes a leading-edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, a rear panel arranged at least partially arranged at a distance to the inner surface, a closed chamber inside the leading-edge structure, a heating device attached inside the chamber, and an air conveying device in fluid communication with the heating device. The air conveying device is configured to convey air from inside the chamber through the heating device to be heated and returned to the chamber, such that a circulating flow of heated air is created inside the chamber.

Abstract: Methods, systems, apparatus, and articles of manufacture to damp catapult loads on an aircraft are disclosed. An example apparatus disclosed herein includes a launch bar including a first portion and a second portion, the first portion to be releasably coupled to an aircraft catapult, the second portion to be releasably coupled to an aircraft catapult system, and a damper operatively coupled between the first and second portions, the damper to reduce longitudinal forces applied to the launch bar at the first and second portions when the aircraft is launched by the aircraft catapult.

Abstract: The present disclosure discloses a landing aid for a parachutist, in particular for a tandem jump or landing with heavy equipment, having an air bag, which protects the parachutist during landing, wherein the air bag has an inflow opening through which air can flow into the air bag in order to fill it by means of the airstream. It is provided that the landing aid comprises a spring element, by means of which the inflow opening is held in the correct position with respect to the air flow and/or an unpacking process of the air bag is supported.

Abstract: The present disclosure relates to a system for recovering an aerial target by using a mechanical arm actuator in a non-bearing mode. The system includes: a hanging rack, a catcher, hung on the hanging rack and configured to catch a target; a guide arm, configured to guide the catcher to catch the target; a states observation apparatus, configured to observe a state of the target; and a controller, electrically connected to the states observation apparatus and the guide arm, where the controller obtains the state of the target through the states observation apparatus, and controls the guide arm to guide the catcher to catch the target in time.

Abstract: A pneumatic actuator can include a housing and an actuator shaft disposed within the housing and configured to actuate between a first position and a second position. The pneumatic actuator can include a single bushing located within the housing between the housing and the actuator shaft. The single bushing can be configured to support the actuator shaft without the actuator shaft being supported at a second location while allowing actuator motion under set operating conditions.

Abstract: A device for actuating an aircraft undercarriage leg includes an electronic controller and an actuator. The actuator includes a three-phase electric motor connected to the electronic controller. The device is arranged to authorize gravity deployment of the aircraft undercarriage leg. The motor includes a stator having at least first and second star-coupled three-phase windings. The electronic controller includes a first control channel connected to the first three-phase winding, and a second control channel connected to the second three-phase winding. Each of the control channels includes a controller that generates a high-level control instruction, a driver that generates a low-level driver instruction from the high-level control instruction, and a braking circuit that brakes the motor during the gravity deployment of the leg by using energy produced by the motor. The device is arranged to use the control channels as a function of the availabilities of the components of each channel.

Abstract: An unmanned aerial robotic vehicle (UARV) that can fly to an object such as a palm tree, hover in place adjacent to the object, mount itself securely and releasably to a mounting location on the object using a mounting mechanism, and which uses an incorporated utility system for performing one or more utilitarian functions, such as use of a cutting tool to trim palm tree branches and foliage.

Abstract: An apparatus that includes a munitions dispenser comprising a plurality of flicker assemblies. The flicker assemblies include a flicker arm and a guide wall arranged in a circular pattern.

Abstract: The heat exchanger can include one or more Helmholtz resonator having a cavity internal to the skin of the vehicle, the cavity delimited by a wall, the Helmholtz resonator having an aperture formed across the skin and fluidly connecting the cavity to the atmosphere, the cavity extending in the forward orientation of motion relative the aperture, an open cell structure filling at least a portion of the cavity; and a fluid passage internal to the skin, the fluid passage in thermal communication with the cavity via the wall of the cavity.

Abstract: An apparatus may include: a support base; and two or more roller wheels, each adjustable in orientation, position, or orientation and position, mounted on the support base and configured to engage with an object in a passive locking configuration. The apparatus may be further configured to disengage from the object in the passive locking configuration. The apparatus may be further configured to lock the object to the apparatus in an active locking configuration. Orientations, positions, or the orientations and positions of the at least two of the two or more roller wheels may be adjustable.

Abstract: According to one embodiment, a flying body includes a radar, a supporter, a plurality of rotors supported by the supporter, and a controller. The rotors include a first rotor. The radar is configured to perform a detection operation and a non-detection operation. The controller is configured to perform a first control operation in a first transition from the non-detection operation to the detection operation. The controller is configured to perform a first change in the first control operation to change a rotational speed of the first rotor from a rotational speed of the first rotor in the non-detection operation. The detection operation is performed after the first control operation.

Abstract: A piloting device for piloting an aircraft includes a piloting member suitable for being actuated by a pilot, a mechanism for mounting and guiding in rotation the piloting member about at least one rotation axis with respect to a frame, at least one force sensor connected between the piloting member. The mechanism includes at least one sensing element configured to produce a signal upon deformation indicative of a force applied to the piloting member. The force sensor comprises at least one pair of bearing surfaces. The device also includes at least one pair of stops configured to limit the angular amplitude of rotation of the piloting member with respect to the frame on abutment of the at least one pair of bearing surfaces with at least one pair of stops. The stops or at least one of the bearing surfaces comprises a compliant material.

Abstract: A fall protection system and method, particularly for attenuating shocks transmitted to a person's body by a safety line, such as a rope or cable, after a fall or while being deliberately lowered from an overhead anchor point. A shock absorber assembly is incorporated in or on the safety line, deployed between the person and the safety line anchor point.

Abstract: A method for manufacturing at least a portion of a box structure obtained from an outer skin and a plurality of sections each having a joining face in contact with the outer skin. The method comprises a step of positioning the sections on a mold, a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin, a step of placing a central portion of the fiber preform on the sections positioned on a first face of the mold and a step of forming a lateral extension of the fiber preform to press the fiber preform against a forming surface. A central wingbox obtained by the method is provided and a forming tool for carrying out the method.

Abstract: Disclosed is a lumbar support system enabling the lower back to recoil during open canopy descent. The system includes at least one lumbar strap linked by a front link to the lower part of the main lift webs and arranged in such a way that same is adapted to be linked at least in one point to the back straps when arranged in a “V” shape at the rear of the parachute pack, or in two spaced-apart locations when arranged separately. After the main parachute opening, the angular pivoting of the lumbar strap performed by the transfer of the load onto the back of the user increases the respective spacing of the two main lift webs, which allows the lower back to recoil.

Abstract: Flaperon actuation systems for aircraft are disclosed herein. An example aircraft includes a wing including, a fixed wing portion, a flaperon, and an actuation system. The actuation system includes a first actuator coupled to the fixed wing portion. The first actuator is operable to move the flaperon along a first degree of freedom between a stowed position in which the flaperon is aligned with the fixed wing portion and a deployed position in which the flaperon is moved downward relative to the fixed wing portion. The actuation system also includes a linkage assembly coupled between the fixed wing portion and the flaperon. The linkage assembly includes a second actuator operable to move the flaperon along a second degree of freedom to pitch the flaperon between an upward position and a downward position.

Abstract: The present application proposes an airborne electromagnetic signal observation device and a system carried by an unmanned aerial vehicle (UAV). The device includes an inner frame, an outer frame and a flexible support that are connected to each other. The device and the system can enhance the stability of the sensor in flight and greatly suppress motion noise.

Abstract: An aircraft seat frame for supporting at least one human individual may include a contiguous plate having a first end and a second end; a first bend in the contiguous plate, the first bend spaced from the first end, thus defining a back support portion extending between the first end and the first bend; a second bend in the contiguous plate, the second bend spaced from the first bend, thus defining a seat portion extending between the first bend and the second bend; and a third bend in the contiguous plate, the third bend spaced from the second bend and from the second end, thus defining a leg portion extending between the second bend and the third bend and a base extending from the third bend to the second end.

Abstract: There are provided a safety apparatus and an aerial vehicle including the safety apparatus, in which a lid and an opening end of a container are fixed before operation more firmly than a conventional art to be less susceptible to an external environment. A safety apparatus includes a piston member, a cylinder that accommodates the piston member and is provided with a bore through which the piston member protrudes to the outside during operation, a push-up member that is pushed up in one direction by the piston member, an ejected object 16 that is pushed up while being supported by the push-up member, a gas generator that moves the piston member in the cylinder, and a lid 21 including a projection 21a. The projection 21a includes a second through hole 21c, and an engagement mechanism is configured when a pin member 22 is inserted into the second through hole 21c and a first through hole 18a provided in a container 18 to engage an opening end of the container 18 and the projection 21a.

Abstract: Disclosed herein are parachute canopies and sliders for use with parachutes. The parachute canopies can include one or more deformable vent panels that can be used to control an inflation rate of the canopies based on an internal pressure within the canopies. The sliders can include strips that form through holes that have a width that distributes a radial load on suspension lines and allow for the use of lower weight, high modulus suspension lines.