Abstract: An environmental control system (ECS) for a multi-engine aircraft includes a controller configured to switch the ECS between a plurality of operating modes. The plurality of operating modes includes a first operating mode configured to receive bleed air from each engine of the aircraft in a first environmental condition, wherein the pressure of the bleed air is about equal from each engine. The plurality of operating modes includes a second operating mode configured to receive bleed air from at least one engine of the aircraft in a second environmental condition, wherein the pressure of the bleed air is different between at least two engines.

Abstract: A multilayer structure for deicing an aircraft airfoil component includes an electrically and thermally insulating bottom layer formed in a defined pattern directly on the aircraft airfoil component, an electrothermal middle layer of electrically resistant heater element arrays formed in the defined pattern on the electrically and thermally insulating bottom layer, and a thermally conductive and electrically insulating top layer encapsulating the electrically and thermally insulating bottom layer and the electrothermal middle layer of electrically resistant heater element arrays. The multilayer structure may be directly applied to the airfoil component by direct writing/additive manufacturing, and may be done with the assistance of a multi-axis robot.

Abstract: A personal air vehicle may feature an air module that may be attached to a ground module. The air module may be equipped with exit vanes or vectored engine exhaust to provide redundant control effectors to the cyclic or collective pitch of at least one rotary wing under the control of a control system.

Abstract: A folding wing comprises a fixed section, a folding section, and a latch system for latching the folding section to the fixed section. The latch system includes a plurality of latch pins, and a corresponding plurality of non-backdriveable mechanical actuators for extending the latch pins to engage the folding section.

Abstract: A silencer for a shotgun, where the silencer comprises an outer housing and an inner hollow body arranged in the outer housing, where the outer housing comprises a main part and a first and second end part connected to the main part, where the inner hollow body further is provided with a number of longitudinal elevations extending over a length of the inner hollow body and where the longitudinal elevations are arranged at a distance from each other around an inner circumference of the inner hollow body, where it between two adjacent longitudinal elevations and over the length of the inner hollow body are provided a number of openings arranged at a distance from each other.

Abstract: A selective fire firearm may be provided having a fully automatic open bolt and a semi-automatic closed bolt mode of operation. The firearm may include a trigger group having a trigger prop that ensures that, when the trigger is released in the fully automatic open bolt mode, the bolt carrier stops in an open bolt position held by an open bolt sear. The trigger prop may include a foot that, following a first trigger pull in the fully automatic open bolt mode, slides under and props a rear end of the trigger in a position that allows the open bolt sear to catch the bolt carrier when the trigger is released and propped but prevents the trigger sear from engaging the hammer.

Abstract: Trigger groups for semi-automatic firearms have a frame, a hammer connected to the frame and movable between a cocked position and a striking position, the hammer being biased toward the striking position, a trigger element connected to the frame and movable by a user between a forward position and a rearward position, a selector connected to the frame and movable between at least a first position and a second position, a disconnector having a hammer engagement facility adapted to selectably engage the hammer, a disconnector control element movable between a first control position and a second control position, the disconnector being operably engaged to the disconnector control element, the disconnector operable to move in a first range of motion when the disconnector control element is in the first control position, and in a second range of motion when the disconnector control element is in the second control position.

Abstract: An aircraft landing gear assembly includes a structural member coupled to another part by a joint including engagement formations or a relatively high friction coating arranged such that the joint inhibits pivotal movement of the structural member when the structural member is compressively loaded in an axial manner.

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: A semiautomatic pistol having a barrel with an exterior surface that has a plurality of indentations and dimples to dissipate heat and reduce frictional engagement between the barrel and the slide. The barrel component includes a crown portion that is recessed to protect the crown portion by a pocket.

Abstract: The present disclosure relates to a firearm which may include a frame with a first outer wall, and a second outer wall opposite the first outer wall. A laser module may be disposed between the first and second outer walls. An alignment pin may be in communication with the first outer wall and may be configured to move the laser module relative to the frame.

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: A preformed warhead is provided with a casing having a front section and a rear section. A plurality of target piercing fragments is arranged at the front section. The density of a given fragment diminishes the further the given fragment is from a centerline of the warhead. An initiating point located on the centerline is positioned at the rear section of the warhead. An explosive charge is positioned between the initiating point and the target piercing fragments. Upon detonation of the warhead, the explosive wave propagates in a radial fashion such that the fragments receiving the impact of the explosive force soonest and most directly are those fragments closest to the centerline. Thus, a substantially planar velocity profile of all the fragments is achieved.

Abstract: A variable velocity pneumatic launcher including at least one chamber filled with a projectile. The launcher includes a ballast chamber filled with pressurized air selectively released to propel a projectile from the launcher's barrel. The launcher includes a firing chamber filled with ambient air and a ballast chamber filled with pressurized air. A piston rod extends between the chambers and attaches to a firing piston and a ballast piston located inside the firing chamber and ballast chamber, respectively. The rod is connected to an adjustable velocity valve which controls the amount of longitudinal movement of the rod. When the trigger is activated, a portion of the pressurized air from the ballast chamber is delivered to the firing chamber.

Abstract: A tracer insert has an upper cavity for retaining shot and a lower cavity for retaining a tracer powder compound. The tracer insert is configured for placement within the shot-pocket of a wad within a shotgun shell. The shot is placed in and around the tracer insert within the shot pocket and some shot is retained within the upper cavity of the tracer insert. A bottom exhaust port in the lower cavity allows the release of the tracer powder compound upon firing of the tracer shell. A cavity separator separates the upper and lower cavities and a flow channel may extend down from the top of the tracer insert into the lower cavity to allow a flow of air to aid in the release of the tracer powder compound. Side exhaust ports may be configured around the lower cavity to provide additional release area for the tracer powder compound.

Abstract: A nacelle is configured to be coupled to an underside of a wing and forms a clearance space between the nacelle and a leading edge slat of the wing. A portion of an outlet cowling moves longitudinally aft when a reverse thrust configuration is activated and the leading edge slat is deployed toward the nacelle. The outlet cowling also includes another portion located adjacent to the leading edge slat that does not move when the reverse thrust configuration is activated and thus maintains its clearance space from the leading edge slat.

Abstract: An aircraft wing has an upper surface element and a first actuator powered mechanism for varying the shape of the surface element which includes: an upstream segment SEG1, a downstream segment SEG2, an interconnecting segment SEG3 interconnecting a downstream edge of SEG1 with an upstream edge of SEG2, wherein the interconnecting segment SEG3 extends along the whole or at least a major part of the downstream edge of SEG1 and the whole or at least a major part of the upstream edge of SEG2, and a link element LNK interconnecting an upstream edge of SEG1 with an upper surface of the aircraft wing, and the first mechanism interconnecting a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the airfoil. The first mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2.

Abstract: A firearm comprises a frame and firing control housing insert detachably mounted in the frame. A rear securement feature includes a locking slot formed in the rear wall of the insert engaging a locking protrusion formed in the rear wall of the frame which retains the rear portion of the insert in the frame. A front securement feature includes a rotatable pin inserted through holes in the insert front portion and frame. A radial retention protrusion on the pin is interposed between the insert and frame defining an interlock feature. The pin is rotatable into a first position wherein the protrusion passes through a complementary configured frame aperture allowing the pin to be removed, and a second position wherein the protrusion is not aligned with the aperture to engage the frame and prevent pin removal.

Abstract: Particular embodiments include a non-dedicated, temporarily installed, airborne special mission payload mounting system comprising a pressurized door plug assembly installed in an opening on the side of an aircraft fuselage. A rotationally-actuated strut extends from a first end connected to an interior of the aircraft fuselage, through the pressurized door plug assembly, to a second end of the strut connected to one or more payloads. The rotational axis of the strut is exterior to the aircraft fuselage.

Abstract: A self-glowing solid material comprises a man-made metal mixture containing at least one rare earth metal and an oxide of iron. The material is inducible by flame initiation to self-glow with yellow-to-red colors (577-to-700 nanometer wavelengths). A stealth tracer ammunition comprises a projectile body having a tip and a base, and a solid pellet disposed in the base. The pellet may be made from the above-mentioned self-glowing solid material or another suitable material. The pellet becomes incandescent as a result of being heated when the ammunition is fired. The incandescent pellet emits a glow observable only from behind when the ammunition travels downrange after being fired. An illuminant comprises a bimodal blend of a man-made metal mixture containing at least one rare earth metal and an oxide of iron. The bimodal blend is a blend of smaller-sized fragments and larger-sized pellets. The illuminant is capable of ignition and dispersion in response to ballistic energy to create illumination.