Abstract: Systems, equipment, and methods to deposit energy to modify and control shock waves and hypersonic or supersonic fluid flow, including systems for controlling, mitigating, and/or effecting air flow in relation to air vehicles, wind tunnels, or other assets, or the like, as well as systems, equipment, and methods for disrupting the shock structure at the inlet for the engine of an air vehicle traveling at supersonic or hypersonic speed; mitigating blast effects on vehicles; mitigating heating of throats in supersonic and hypersonic wind tunnels, as well as control the flow parameters and Mach number in their test sections.

Abstract: A device responsive to an acceleration pulse event, the device including: a piezoelectric device configured to generate a voltage over a duration responsive to one or more acceleration pulse events; an electrical storage device configured to receive a portion of the generated voltage to accumulate a charge; an energy dissipating device coupled to the electrical storage device and configured to dissipate the accumulated charge following the one or more acceleration pulse events and not to substantially dissipate the accumulated charge during the one or more acceleration pulse events; and a voltage limiting device coupled to the electrical storage device and configured to limit the portion of the generated voltage applied to the electrical storage device to a predetermined limit.

Abstract: An apparatus and method for aerial recovery of an unmanned aerial vehicle (UAV) are provided. The apparatus includes a rigid base having a first section and a second section, wherein the first section is securely mounted to a floor of an aircraft. The apparatus further includes a servicing platform moveably mounted to the base and configured to move along a direction parallel to a longitudinal axis of the aircraft such that in an extended position, the servicing platform at least partially protrudes from a rear cargo door of the aircraft, wherein the servicing platform comprises a capturing mechanism configured to capture the UAV in the extended position.

Abstract: An electrical energy harvesting device for harvesting electrical energy from a pulsed impact loading event. The device including: a piezoelectric element configured to be loaded and unloaded to a first load level by the pulsed impact loading event; and a first inductor coupled to the piezoelectric element configured to be loaded and unloaded to a second load level by the pulsed impact loading event, wherein the piezoelectric element and the first inductor together operate as a first inductor/capacitor (LC) resonant circuit having a first resonance frequency and wherein the loading of the first inductor lags in time the loading of the piezoelectric element.

Abstract: In particular embodiments, a mission payload mounting apparatus comprises a pressurized door plug assembly on a side of an aircraft fuselage and a strut having a first end and a second end. The strut extends from an interior of the aircraft fuselage through the pressurized door plug assembly to an exterior of the aircraft fuselage. The strut is capable of being rotationally actuated about an axis exterior to the aircraft fuselage. The first end of the strut is connected to the interior of the aircraft fuselage. One or more payloads are attached to the strut between the axis and the second end.

Abstract: An apparatus for launching a payload includes a primary barrel, a primary projectile including a secondary barrel, and a secondary projectile including the payload. Prior to firing the apparatus to launch the payload, the primary projectile is contained within the primary barrel, and the secondary projectile is contained within the secondary barrel. Ignition, detonation, or expansion of a primary propellant within the primary barrel launches the primary projectile from the primary barrel. Ignition, detonation, or expansion of a secondary propellant within the secondary barrel launches the secondary projectile from the secondary barrel. The secondary projectile can further include a volume of a secondary explosive material; detonation of the secondary explosive material propels at least a portion of the payload away from a remainder of the secondary projectile. The payload can include cremation remains, DNA, or text, images, or other information.

Abstract: An apparatus implementable on a firearm may include a takedown pin and a pivot pin. The takedown pin holds together a rear portion of lower and upper receivers of the firearm. The pivot pin holds together a front portion of lower and upper receivers of the firearm. Each of the takedown pin and pivot pin respectively includes a head and a generally cylindrical shank extending from the head toward a distal end thereof opposite the head. The shank is configured with: (1) a first groove track extending along a longitudinal axis of the shank, (2) a second groove track parallel to the first groove track and extending along the longitudinal axis of the shank, and (3) a linking groove track extending around the longitudinal axis of the shank and linking the first groove track and the second groove track.

Abstract: A system for maintaining a machine. The system includes an aerial vehicle configured to fly to a lubrication location proximate the machine. A supply of friction minimizing material is carried by the aerial vehicle. A controller is configured to deliver at least part of the supply of friction minimizing material to the machine when the aerial vehicle is at the lubrication location.

Abstract: The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

Abstract: A semi-automatic or automatic rifle comprising a barrel attached to and upper receiver and including a compressible bolt carrier extension system. The compressible bolt carrier extension system includes a bolt carrier, an extension spring, two pins, and a reciprocation bolt carrier extension piece. As a whole, the compressible bolt carrier extension system makes possible the use of elongated upper and lower receivers to be used for chambering long-action or other center fire cartridges for use with AR rifles such as the M-16, and M4 etc., eliminating the need for any buffer or buffer tubes other than those commercially available. A further advantage of the compressible bolt carrier extension system is the reduction of felt recoil as the system fully loads during the recoil stroke as it pushes against the buffer absorbing additional recoil energy. The system can be incorporated into firearms using a variety of cartridges.

Abstract: Gobo projection targeting devices have a light source, a lens assembly associated with the light source, the lens assembly having a first element, a second element, and an aiming figure, the first element being closer to the light source, and the second element having a smaller diameter than the first element, such that a first portion of light emitted by the light source and transmitted by the first element will bypass the second element and a second portion of light emitted by the light source and transmitted by the first element will not bypass the second element. The first and second elements may each be converging lenses. The second element may be adapted to generate an image of the aiming figure away from the illuminator. The first portion of light may be a field illumination pattern lacking a focused image. The lens assembly may be movable.

Abstract: A magazine loader apparatus and method includes in one embodiment, a magazine holder where the magazine holder is configured to removably hold a magazine and where the magazine holder includes a loading chamber configured to receive a bullet. A loading arm connected with the magazine holder, a plunger connected with the loading arm, and a bullet loader where the bullet loader is configured to temporarily hold the bullet and where the bullet loader is removably connectable with the magazine holder at the loading chamber such that the bullet exits the bullet loader into the loading chamber.

Abstract: A flying drone, which includes a fuselage; a propulsion powered at least by electrical accumulators and/or photovoltaic cells; and first and second wings. The first wing is defined by a wingspan and by an upper surface area, where the upper face of the first wing is essentially covered by photovoltaic cells. The second wing has practically the same wingspan and upper surface area as the first wing. The second wing is offset along the fuselage and in height relative to the first wing. The upper face of the second wing is essentially covered with photovoltaic cells.

Abstract: A magazine loader for loading cartridges into a magazine includes a base and a housing supported by the base. The base and the housing support a bowl for receiving a plurality of cartridges. A wheel is disposed inside the bowl cavity defined by the bowl. Cartridges are circulated in the bowl upon rotation of the wheel and exit the bowl via an aperture while the cartridges are assuming either a first orientation or a second orientation. A series of cartridges having random orientations are fed to a sorter of the magazine loader. The sorter is operable to receive a first cartridge and rotate the first cartridge clockwise 90 degrees if the random directional orientation of the first cartridge is the first directional orientation and/or rotate the first cartridge counterclockwise 90 degrees if the random directional orientation of the first cartridge is the second directional orientation.

Abstract: A blanket assembly for use in at least one bay and with at least one frame member of an aircraft, the assembly including an insulation blanket. The insulation blanket includes a bay section sized and shaped to fit within the bay and of sufficient thickness to provide insulation to the bay, a return section disposed on a first side of the bay section; and a cap section disposed on a second side of the bay section, opposite the first side. The cap section is sized and shaped to at least partially cover the frame member when the cap section is wrapped around the frame member, the cap section being of sufficient thickness to provide insulation to the frame member. The bay section, the return section, and the cap section are of unitary construction.

Abstract: Provided is a handguard attachment mechanism for use with a firearm using a standard AR-pattern barrel nut having a substantially cylindrical portion with an axial length and an enlarged diameter radial flange at a forward end. The handguard includes a substantially tubular handguard with proximal and distal ends. The proximal end includes a longitudinal slot extending from the proximal end toward, but not to, the distal end. A pair of clamping lugs, one positioned on each side of the slot adjacent the proximal end, have means for adjustably drawing the clamping lugs together to narrow at least a portion of the longitudinal slot. A circumferentially incomplete barrel nut bushing is configured to fit on the barrel nut.

Abstract: Openings in a muzzle brake provide recoil inhibition and impulse noise attenuation by redirecting the propellant gases to the external environment. A turning vane aggressively turns and redirects the propellant gases in a rearward direction to counter the recoil of the weapon system. An angled baffle provides a physical barrier to redirect propellant gases rearward to provide additional force to counteract the recoil force. Attenuation slits mitigate blast overpressure by producing a fluid barrier of high velocity propellant gases directed radially away from the muzzle brake. The fluid barrier from the attenuation slits interacts with the redirected propellant gas from the turning vane and the angled baffle and redirects the counter recoil gases away from the crew.

Abstract: The invention relates to a gun, especially an air gun or firearm, comprising a barrel arrangement (1) that has at least one barrel element (2) forming at least part of a barrel of the gun, and a silencer element (3) that is or can be fastened to the barrel element (2); in order for the silencer element (3) to be fastened to the barrel element (2), at least one clamping element (12) that can be or is fastened within the silencer element (3) is used to be able to axially clamp or axially clamp the silencer element (3) against at least one contact element (5) located or formed on the barrel element (2).

Abstract: A novel locking mechanism for a noise suppressor mount for a firearm comprising a muzzle attachment comprising a plurality of locking positions, a collar, and a locking arm comprising a locking notch wherein the collar rotates to move the locking notch in a circular direction into a locking position.

Abstract: The invention relates to method for pre fragmentation of a warhead (1) comprising a warhead body (2), an explosive charge (6), a fin part (3), and a warhead shell (4) with the density ?shell wherein the warhead shell (4) comprises pre formed cavities (5), where each cavity (5) comprises at least one pre formed projectile (7) with the density ?proj and filler material or agent (8) with the density ?fill, wherein the method comprises the following steps: —pre formation of the cavities (5) in the warhead shell (4), —arrangement of at least one projectile (7) in each pre formed cavities (5), —filling of filler material or agent (8) in the cavities (5) so that the cavities (5) are filled, —treatment of the filler material or agent (8) so that the filler material or agent (8) forms a connected structure vid high adhesiveness to the projectiles (7) and to the walls of the cavity (5). The invention further relates to a pre fragmented warhead.