Abstract: A life vest device, for a fixation on one or more aircraft seats, with a life vest unit, which is embodied as a lift vest with a packaging unit for a sealed accommodation of the life vest unit and with an opening unit for an opening of the packaging unit, which features one or more pull straps. The opening unit is functionally connected with the life vest unit and the packaging unit comprises one or more fixation units for a fixation on an aircraft seat. For a retrieval of the life vest unit from the packaging unit, the opening unit is connected in a tear-proof manner with the life vest unit. The pull strap and the life vest are embodied integrally with each other.

Abstract: An aircraft ejection seat assembly is disclosed where a survival kit is incorporated into a seat back of an ejection seat, and that is released from the ejection seat by one or more actuators. The survival kit is attached to the parachute lines. One or more retention pins may secure the survival kit relative to the seat back. Representative actuators that may be used to move the retention pin(s) to a release configuration including mechanical (e.g., a bell crank), electrical (e.g., a controller such as a MASS), or pressurized fluid.

Abstract: Described herein are features for a high altitude lighter-than-air (LTA) system and associated methods. The LTA may include a super-pressure balloon (SPB) and/or a zero-pressure balloon (ZPB). The SPB may include two, three, four or more chambers. There may be more than one SPB. The SPB may use a compressor to provide a variable amount of ballast air by pumping in or expelling out ambient air. The zero-pressure balloon (ZPB) may be attached with the multi-chamber SPB. The ZPB may provide lift for the system. The SPB may include lifting gas and ballast air to provide both lifting and descent functions. The SPB may have an internal barrier separating a lift gas compartment from a variable ballast air compartment.

Abstract: A payload coupling apparatus is provided that includes a housing having an upper portion, a lower portion, and a side wall positioned between the upper and lower portions, an attachment point on the housing adapted for attachment to a first end of a tether, a slot in the housing that extends downwardly towards a center of the housing thereby forming a hook or lip on the lower portion of the housing beneath the slot, a plurality of holes in the upper portion of the housing; and a plurality of holes in the lower portion of the housing. A method of retracting a payload coupling apparatus during UAV flight is also provided.

Abstract: Methods and systems according to one or more examples are provided for reducing chatter in a no-back brake during aiding load operations. In one example, an apparatus comprises a no-back brake, disposed within an actuator coupled to an aircraft, including a shaft, and a ball ramp plate, coupled to the shaft, to receive a force comprising an air loading force and is displaced responsive to the force. The apparatus further comprises a brake, coupled to the shaft and coupled to the ball ramp plate, and displaced by the ball ramp plate corresponding to a distance the ball ramp plate is displaced. The apparatus further comprises a modulating spring, coupled to the shaft and coupled to the brake, configured to compress in response to the brake being displaced, and the modulating spring is configured to apply a selective compressive force at the brake corresponding to a distance the brake is displaced.

Abstract: Segmented shields are disclosed comprising material combinations and rolled configurations to impede and mitigate through-and-through penetration damage of a structure incorporating the segmented shields from the damage resulting from the impact of high-velocity micro-meteoroids and orbital debris particulate.

Abstract: A support mechanism that has a body, a motor located on the body, a first rod that is triggered by the motor so as to be able to rotate clockwise or counter clockwise around its own axis, a transfer member connected at one end to the first rod, a second rod connected to the transfer member is able to make a radial rotational movement around its own axis together with the first rod by the transfer member, a holder that is located on the body surrounds the second rod and is able to rotate around its own axis and move linearly along a direction that the second rod extends, and at least one bearing that is located on the second rod moves towards or away from the weight upon triggering of the first rod by the motor and contacts the weight for supporting the weight from at least one point.

Abstract: A delivery drone apparatus for automatically delivering packages includes a drone body having a body cavity. A pair of landing skids is coupled to the drone body. A battery, a CPU, and a GPS are coupled within the body cavity. A transceiver is coupled within the body cavity and is in operational communication with the battery, the CPU, and the GPS. The transceiver is configured to communicate with a smartphone. At least one camera is coupled to the drone body. The camera is in operational communication with the battery, the CPU, the GPS, and the transceiver. A plurality of motors are coupled to the drone body. Each motor has a propeller and is in operational communication with the battery and the CPU. An electromagnet is coupled to the drone body. A package magnet is selectively engageable with the electromagnet and is configured to be coupled to a package.

Abstract: A truck assembly for aircraft landing gear is provided. The truck assembly includes a hinge connecting a truck beam to a strut of the landing gear. The hinge is configured to allow the truck beam to rotate about the hinge relative to the strut transversely with respect to the length of the truck beam to thereby pivot the truck assembly relative to the strut between a landing position and a stowing position.

Abstract: A system utilizing an antenna generating an electromagnetic (EM) wave to interact with a solar EM wave to streamline magnetic flux in the polar cusp and to facilitate the flow of solar plasma through the Polar Cusp, resulting in an elevated plasma flux at the exit of the Polar Cusp. The elevated plasma flux intercepts and removes small space debris from Low Earth Orbit (LEO), Geosynchronous Earth Orbit (GEO) and Geosynchronous Transfer Orbits (GTO) transiting the LEO altitude regimes.

Abstract: A control system (400) for an active inceptor (103) for a fly by wire aircraft permits a zero force null point to settle to a non-zero displacement trim position. An internal position state of a second order mass spring damper model is moved in conjunction with force-displacement characteristic coordinates. This results in no second order dynamics being superimposed on the feel of the inceptor (103) when dynamically adjusting the trim position, thereby eliminating the possibility of any unpleasant buzzing been felt by the operator of the inceptor during a trimming operation.

Abstract: A system is described and includes a rack for carrying payload disposed in payload bay; a rack extension assembly for affecting linear displacement of the rack between a first position in which the rack is stowed within the payload bay and a second position in which the rack is supported outside the payload bay; a payload actuator system for selectively causing the rack extension assembly to move the rack between the first and second positions; a payload bay door; and a door actuator system for selectively opening and closing the payload bay door.

Abstract: An insect catching device may include at least two insect capture surfaces, a first surface including a first color, and a second surface including a second, lighter color relative to the first color of the first surface. The second color of the second surface may highlight the presence of insects captured thereon facilitating at least one of ease of counting and ease of identification of captured insects. The insect catching device may also include a line of weakening disposed between the first surface and the second surface. The line of weakening may include at least one perforation. The second surface may be detachable from the first surface along the line of weakening. The first color may be configured to decrease visibility of captured insects on the first surface observable by a viewer through an insect trap cover.

Abstract: The Guideless Resilient Androgynous Serial Port (GRASP) mechanism provides an androgynous mechanical and electrical interface that can be tailored to the meet the requirements of a given application. Each mechanism is equipped with physical connections (spring pins) for both power and data transmission between modules.

Abstract: A canopy fragilization system for use in an aircraft ejection system may comprise: a sharp breaker disposed on a first side of an ejection seat, the sharp breaker configured to act as a primary breaker of a canopy of an aircraft; a blunt breaker disposed on a second side of the ejection seat, the blunt breaker configured to act as a secondary breaker of the canopy of the aircraft; and a deployable overhead protection assembly comprising a mitt extending forward of the sharp breaker and the blunt breaker when in a deployed position, a forward end of the mitt configured to act as a tertiary breaker of the canopy of the aircraft.

Abstract: An airplane rudder and brake pedal assembly includes a rudder arm assembly having one rudder arm with first upper and lower arm portions, and another rudder arm with second upper and lower arm portions. The rudder arm assembly is assembled to a beam at an intersection of the first upper and lower arm portions, and an intersection of the second upper and lower arm portions. The first and second rudder arms are configured to rotate about the beam at the intersection. The rotation of the first and second rudder arms is configured to adjust control surfaces that control a yaw axis of the airplane. A brake pedal is attached to the first and second lower arm portions. Rotation of the brake pedal brakes the airplane. A rotary sensor is assembled to the brake pedal and the lower arm portion, and configured to determine an extent of the brake pedal rotation.

Abstract: The technology relates to techniques for drogue deployment for a lighter than air (LTA) vehicle descent. A drogue deployment system for an LTA vehicle descent can include a drogue comprising a drogue parachute coupled to a carrier. A spring can be configured to launch the drogue from a launch tube directed outward from an apex of the LTA vehicle in an acute angle from a horizontal plane. A core can be placed around the launch tube and placed around the spring, the core compressing the spring and holding the spring in a compressed state prior to deployment, and a riser can couple the carrier to the envelope of the LTA vehicle. In some cases, the drogue deployment system can comprise two or more drogues, wherein intervals between the two or more drogues can be selected such that horizontal components of drogue deployment forces approximately cancel out.

Abstract: The utility model relates to an unmanned aerial vehicle and an undercarriage thereof. The undercarriage includes: a power assembly disposed within a fuselage, the power assembly including a first connecting member and a drive apparatus configured to drive the first connecting member to perform a reciprocating linear motion; and an undercarriage body connected to the power assembly, the undercarriage body including a first connecting rod hinged on the first connecting member, and a second connecting rod of which one end is hinged on the power assembly and the other end is hinged on the first connecting rod. When the first connecting member performs the reciprocating linear motion, the undercarriage body is driven to be unfolded or folded into the fuselage. The utility model further relates to an unmanned aerial vehicle. For the foregoing unmanned aerial vehicle and the undercarriage thereof, the power assembly may be used to drive the undercarriage body to switch between an unfolded state and a folded state.

Abstract: An aircraft ejection seat sequence may comprise: a sequence controller; a sensor target; and a non-contact sensor in electrical communication with the sequence controller, the non-contact sensor configured to transmit a reference control signal to the sequence controller in response to sensing the sensor target.

Abstract: High-lift systems and related methods are described. An example apparatus includes a fixed wing and a Krueger flap movably coupled to the fixed wing between a stowed position and a deployed position. The Krueger flap includes a first flap portion movably coupled to the fixed wing and a second flap portion movable coupled to the first flap portion. The first flap portion moves relative to the second flap portion between a retracted position and an extended position. The first flap is to move to the retracted position in response to the Krueger flap moving to the stowed position. The first flap is to move to the extended position to define an aerodynamic surface in response to the Krueger flap moving to the deployed position.