Abstract: A system for monitoring the state of an unmanned aircraft includes a first communication unit, a second communication unit that can be integrated within the aircraft, a state transmission unit that can be integrated within the aircraft for transferring state data of the aircraft, a receiving unit integrated within the aircraft for receiving control commands, a computing unit assigned to the aircraft for validating the state of the aircraft, and an external control and monitoring unit connected to the computing unit. The computing unit executes a simulation model of the aircraft, which is based on numerical integration of a system of equations with a simulation state vector. The computing unit sends a warning signal to the control and monitoring unit on the occurrence of one or repeated instances of a model error correction term exceeding specified interval limits.

Abstract: A brace for stabilizing a handheld device such as a handgun against a user's forearm includes a vertically elongated body adapted to detachably engage a portion of the handheld device, and an arm pivotably connected to a portion of the body. The pivotable arm is selectably moveable between a stowed position wherein the arm is vertically aligned with the body, and a deployed position wherein the arm provides a surface against which a user's forearm is removably receivable to stabilize the handheld device when the body is engaged with the handheld device.

Abstract: The present disclosure provides a release launching system that is operative to receive and retain a drone or other payload in a protected launcher. The launcher helps to reduce the drag of the payload and to protect the payload from environmental factors. The payload is launched when a force initially separates the payload from the launcher and exposes a force generating mechanism. The force generating mechanism may be within the body portion of the device and generate an additional force to assist in separating the payload from the launcher. The payload may be launched using a biasing and fastening mechanism, which may include detachably coupling bracket, to allow for the separation of the payload from the launcher.

Abstract: A lightweight energetic weapons pod 2 that integrates to unmanned aerial systems 1 that enables the operator the ability to engage targets without flight degradation. The device utilizes an energetic weapons pod 2 that may be reloaded to support sustained combat operations. The ability of the device to function as intended is based on explosive mitigation compression zones and recoilless configurations that allow drone survivability during detonation events.

Abstract: A restraint arrangement for an inflatable slide may comprise a releasable restraint and a yoke coupled to the releasable restraint. The yoke may comprise a first strap and a second strap. A first dampener may be coupled to the first strap. A second dampener may be coupled to the second strap. The first dampener and the second dampener may deform in response to a tensile load.

Abstract: An aircraft passenger seat is proposed, having an enclosure and a base component of a backrest of the aircraft passenger seat, wherein the base component assumes an upright position during the use of the backrest. According to the invention, a securing device is provided for releasably securing the base component in the upright position, wherein a securing element of the securing device is adjustable from a securing position of the securing element on the securing device into a release position of the securing element, wherein, in order to lock the securing element in the securing position, a movable locking member of the securing device comes to bear against a latching contour on the securing element in such a manner that the securing element is locked in the securing position.

Abstract: A spacecraft refueling and storage system comprising a first tank and a second tank for storing propellant, a rotatable shaft to which the first and second tanks are mounted for rotating the first and second tanks about an axis of the shaft, and a drive motor for rotating the shaft so that upon rotation of the first and second tanks, liquid propellant is separated from gas in the propellant and settled to an outer portion of the first and second tanks.

Abstract: This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

Abstract: The invention relates to an aircraft passenger seat comprising a support framework, the support framework being designed to be fastened to a floor in an aircraft passenger cabin, wherein the support framework has a seat divider and bars running transversely to the seating direction, the seat divider being supported by the bars. A housing comprises a structural component and the housing at least partly surrounds a backrest. According to the invention, the seat divider is connected to the structural component via a connecting device, the connecting device being designed as a plug-in connection.

Abstract: Various embodiments of the present invention relate to an unmanned aerial vehicle (UAV) and method for operating the same, and an automated guided vehicle (AGV) for controlling movements of the unmanned aerial vehicle.

Abstract: A lug assembly can include a frame, lug base, lug, and door. The lug assembly can be attached to a projectile that can be coupled and decoupled to an aircraft via the lug assembly. The frame can slidably receive the door. The lug can connect to the lug base and rotate thereabout from a first lug position to a second lug position upon the projectile decoupling. In the second lug position, the lug is contained within the frame such that an aerodynamic profile of the projectile is preserved. The door can connect to the lug base via a closing mechanism including one or more tension mechanism that apply a closing force to the door. Upon the projectile decoupling, the closing force causes the door to slide from a first to a second position, the door transitioning the lug to the second lug position and substantially sealing the frame opening.

Abstract: A cockpit pedestal and an aircraft with a cockpit pedestal. The cockpit pedestal includes an integrally-formed frame including an instrument receiving portion defining a plurality of compartments for receiving instruments therein; and a plurality of legs supporting the instrument receiving portion, the plurality of legs being integrally formed with the instrument receiving portion, the plurality of legs being adapted for transferring a load of the plurality of instruments from the instrument receiving portion to a floor of the aircraft cockpit when the cockpit pedestal and the instruments are installed in the aircraft cockpit. In some versions the cockpit pedestal includes a conductive layer electrically grounding the instruments in the cockpit.

Abstract: A protection system for a classroom or other space to protect against a terrorist. The system includes a fixed control unit and a mobile control unit. The fixed control unit contains a hanger for drones to be launched against the terrorist. The fixed control unit also includes data storage units, a computer, a computer program and a memory, power storage units, a sighting laser for obtaining location information about the terrorist and an etching laser for marking the terrorist, an optics system for receiving visual information, and a telecommunication unit to send and receive information. The mobile control unit is worn by a protecting person in the space and includes some of the same components as the fixed control unit. It also has a local aiming system that includes for example a rifle type sight. The drone is a self-contained, self-propelled robotic flying vehicle that can be very small or even the size of a mouse. It has a mag-lev engine, electrical storage units and an aeronautically shaped body.

Abstract: This disclosure provides a stackable propellant module for use inside of a gas generation canister. The modules are designed to enable them to be individually fired rather than as a unitary mass, as done in conventional configurations. This enables the generation of a controlled pressure profile rather than an uncontrolled pressure profile determined by the environmental conditions downhole, such as temperature and pressure.

Abstract: Break barrel airguns are provided with a loading system that uses the cocking action of the break barrel type airgun to load projectiles from a magazine held by a magazine holder into a shuttle system that is positioned by the magazine holder during loader and moved to a position aligned with the barrel during firing. The loading system has a resilient barrier between the magazine holder and the shuttle that reduces the risks of loading errors caused by adhesion between the bolt and a pellet.

Abstract: A system and method for the remote piloting of an electric aircraft is illustrated. The system comprises a remote device located outside an electric aircraft, wherein the remote device is configured to receive a flight command input from a user and transmit the flight command input to a flight controller located on the aircraft. The flight controller is located inside the aircraft and configured to receive the flight command input from the remote device and enact the flight command autonomously as a function of the flight command input.

Abstract: The present disclosure relates to an ejecting system (1) for dispensing countermeasure. The system (1) comprising at least one magazine (2) comprising at least one expendable cartridge (3) and a transporting rack (4) extending in a first direction (D1). Further, the system (1) comprises a magazine feeding mechanism (5) arranged to cooperate with said transporting rack (4) to move each of the at least one magazines (2) from a stored position to a loaded position. Further, the system (1) comprises a dispensing means (6) arranged to hold said at least one magazine (2) when said at least one magazine (2) is in a loaded position, wherein the dispensing means (6) comprises an electrical connector arrangement (7). Moreover, the system (1) comprises a first positioning mechanism (8) arranged to move said dispensing means (6) and the at least one magazine (2) from the loaded position to a protruding position.

Abstract: An upper receiver assembly for a firearm having an upper receiver with an integral barrel nut, a handguard assembly and a barrel nut assembly with a barrel and lock nut is provided. The barrel is received by the upper receiver and is secured directly to the upper receiver using the lock nut. The upper receiver also includes an integral handguard mounting member to which the handguard assembly may be directly attached. The upper receiver assembly allows the user to attach both the barrel and handguard assemblies directly to the upper receiver, independently of one another.

Abstract: The present disclosure relates to a launch system and method. The launch system and method can include at least a preliminary accelerator tube system (PAT) that can be combined with a main accelerator tube system (MAT). The PAT alone or combined with the MAT can be used for launch of a vehicle for testing and/or for delivery of a payload.

Abstract: A floor structure for an aircraft includes a rail that defines a recess having an opening and a bottom and designed to receive one or more attachment elements, a covering element arranged above a segment of the recess so as to provide a complementary bearing surface above the opening, and a cellular supporting structure having a first end that rests on the bottom of the recess, and a second end supporting the covering element. Thus, the covering element can be sufficiently thin to avoid or limit the formation of steps at the surface of the floor structure.