Abstract: A method and apparatus for a boundary layer control device located relative to an aircraft structure. The boundary layer control device has a stowed position and a deployed position. The boundary layer control device moves from the stowed position to the deployed position. A thickness of a boundary layer for the aircraft structure increases in a manner that increases a distance of a heat flow field from the aircraft structure during operation of the aircraft.

Abstract: Containment vessels are adapted to facilitate blast and dispersion mitigation. According to one example, a containment vessel may include at least one containment layer. At least one expansion member may be coupled to the at least one containment layer to apply a force sufficient to expand a perimeter of the containment layer(s) laterally outward. A closure system may be coupled with the containment layer(s), where the closure system is configured to cinch the perimeter of the containment layer(s) around a target object without manual intervention. Unmanned aerial vehicle (UAV) including a containment vessel, as well as methods of making a containment vessel are also disclosed. Other aspects, embodiments, and features are also included.

Abstract: A cartridge magazine is provided. The cartridge magazine may include a rib mounted on a vertical wall of the cartridge magazine. The cartridge may further include a ramp attached to a top of the rib. In another embodiment, the cartridge magazine may include an opening including spacer having a flat portion. The flat portion provides space for a cartridge of a particular caliber between the flat portion of the spacer and an opposing wall of the cartridge magazine.

Abstract: A fin-stabilized sub-caliber projectile adapted to be fired from a rifled barrel, the projectile having a penetrator with a tail fin assembly, a sabot arranged on the penetrator and having at least two sabot segments circumferentially joined to one another that are separated from one another after leaving the barrel by centrifugal forces acting on the projectile during firing. The sabot includes a main body and a front guide flange that is adapted to be supported on an inner wall of the barrel and a rear guide flange arranged at an axial distance. A connecting section of the sabot is arranged between the front guide flange and the rear guide flange and has a smaller outer diameter than the front guide flange or the rear guide flange. The sabot and the penetrator are joined together in a positive manner in a region of the rear guide flange.

Abstract: Disclosed are processes for loading a cartridge such as a shot shell with a shot load and a charge of buffer material. The processes employ a tube that is coaxially aligned with the axis of the cartridge case or shot cup, the tube having an outer diameter that closely fits into the inner diameter of the cartridge case or shot cup. Shot and buffer material are loaded, the leading edge of the tube is inserted to a sufficient depth to cause at least a portion of the shot load and buffer material to rise into the inner volume of the tube, and the tube removed. The insertion-removal cycle effects the efficient mixing of the shot and the buffer material and can be repeated as many times as desired.

Abstract: A system including a coupling (100) configured to couple a hose associated with a tanker aircraft to a nozzle associated with a receiving aircraft. The coupling may include a housing that houses a main poppet and a pilot poppet. The main poppet and the pilot poppet may control fuel flow from the tanker aircraft to the receiving aircraft. The coupling may also include an opening disposed at a first side of the housing. The opening may receive the fuel nozzle. An orifice may be disposed on a second side of the housing, the orifice may permit fuel to flow into the housing. The system may also include a low drag drogue configured to house the coupling. The system may also include a nozzle tip configured to open the pilot poppet and the main poppet, wherein fuel flows to the receiving aircraft in response to the main poppet being open.

Abstract: A universal white room disposed at the distal end of an access arm of a launch pad service tower utilizes multiple interchangeable modular rooms of varying shapes, sizes and configurations to interface with access points on multiple differently configured launch vehicles and/or payload(s). The interchangeable modular rooms attach to a common portal in the white room allowing a single white room to be used. The modular rooms may be stationary relative to the white room or movable relative to the white room.

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: A method of controlling an elevator of an aircraft includes selecting a factor for increasing or decreasing a predetermined horizontal tail load alleviation (HTLA) authority limit for an elevator based on at least one aircraft parameter. The HTLA authority limit decreases with an increase in Mach number and/or airspeed. The method also includes computing an elevator position limit as a product of the HTLA authority limit and the factor, and moving the elevator to a commanded elevator position that is no greater than the elevator position limit.

Abstract: An apparatus and method for securing a landed aerospace vehicle/object onto a landing pad include a use of the magnetic force to couple the landed aerospace vehicle/object with the landing pad. A magnetized base captures and is anchored onto the landing pad. The use of a rocket booster in a high-gravity environment with the ensuring extreme heat exhaust emission considers the use of an exhaust ventilation system.

Abstract: An aircraft nacelle and method of fabricating a monolithic lipskin of the nacelle. The nacelle may include a fan cowl, a bulkhead, and the monolithic lipskin. The lipskin may be formed by spin-forming or explosive forming an annularly-shaped plate onto a mandrel, and machining or chemically-milling integrated stiffeners or other protrusions and attachment tabs into an inner mold line (IML) of the lipskin. The machining or chemical milling may occur before or after the spin-forming or explosive forming. The stiffeners may have a spiral or circumferential configuration. An attachment tab extending from the IML may attach to the bulkhead, such that an outer mold like (OML) of the lip-skin is not disrupted by mechanical fasteners attaching the lipskin to the bulkhead.

Abstract: In one aspect, a sensor system for advanced smart weapons barrels includes one or more sensors, the sensors connected to a processor by way of conductive elements. The smart weapons barrel system may include one or more barrel segments, such segments being removably attached to each other. In certain embodiments, the sensors are positioned along the barrel segments and generate an electrical signal in response to a projectile being fired by the host firearm as the projectile moves past the respective sensor. The processor receives raw data from the sensor signal and may extrapolate and/or calculate further information in order to determine any number of a variety of metrics or other data analysis, including, but not limited to, round count projectile velocity, rate of fire, etc.

Abstract: Disclosed is an autoloading shotgun firearm which shares interchangeable fully compatible modular sub-assemblies, ergonomics, parts commonality, and exterior appearance with the AR rifle platform. Rapidly reversible tool less conversion from rifle to shotgun and vice versa is accomplished by substitution of the AR rifle upper receiver and ammunition detachable magazine with fully compatible shotgun upper receiver and ammunition detachable magazine. Said shotgun utilizes standard rimmed shotgun ammunition via features in the detachable magazine which securely maintain the position and facilitate the feeding of the cartridges during normal operation. No alteration of the AR rifle lower receiver is required. A short-recoil action is integrated into the shotgun upper receiver. The external appearance and functionality of the AR rifle are retained while eliminating the complexity and inherent fouling issues of typical gas systems used in the AR rifle.

Abstract: In one embodiment, an apparatus may comprise an attachment device configured to be embedded in a structure, wherein the attachment device comprises: a body comprising a first flange and a second flange, wherein the body is configured such that the first flange and the second flange are coupled together internally within the body when the attachment device is embedded in the structure; an attachment fitting for coupling a component to the structure in which the attachment device is embedded.

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: Provided herein are shaped charges for focusing a fluid mass and related methods of using the shaped charges for disruption of an explosive target. The shaped charge comprises a plastic shell having a special geometric shape configured to support a shape-conforming explosive. A cylindrical plastic body has an interior volume for containing a fluid and the plastic shell. The plastic body closed distal end has a geometric shape that is substantially matched to the shape of the plastic shell.

Abstract: A blast containment system for trash cans includes a donut-shaped bag having a sealed donut-shaped bottom positioned at the base of the trash can, and an open donut-shaped top positioned and retained at a top periphery of the trash can. An open-ended tubular region extends through the bag between its donut-shaped top and donut-shaped bottom. A rigid container having an open top is disposed in the tubular region of the bag with its open top being coupled to the donut-shaped top of the bag. A liquid fills the bag.

Abstract: An aircraft has an airframe with a two-dimensional distributed thrust array attached thereto having a plurality of propulsion assemblies that are independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto that is operable to tilt about first and second axes responsive to first and second actuators. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector. Responsive to a thrust vector error of a first propulsion assembly, the flight control system commands at least a second propulsion assembly, that is symmetrically disposed relative to the first propulsion assembly, to counteract the thrust vector error, thereby providing redundant directional control for the aircraft.

Abstract: Thermal management system for unmanned aerial vehicles are disclosed. An example housing for an unmanned aerial vehicle includes a central portion defining a cavity. The housing also includes a first arm to support a first propeller. The first arm has a first proximal end coupled to the central portion and a first distal end spaced from the central portion. The first distal end defines an inlet. The first arm defines a first fluid path in communication with the inlet and the central cavity. The housing also includes a second arm to support a second propeller. The second arm has a second proximal end coupled to the central portion and a second distal end spaced from the central portion. The second distal end defines an outlet. The second arm defines a second fluid path in communication with the outlet and the central cavity. The inlet and outlet are in fluid communication via the first path, the central cavity and the second path.

Abstract: Systems, methods, and devices are provided for providing flight response to flight-restricted regions. The location of an unmanned aerial vehicle (UAV) may be compared with a location of a flight-restricted region. If needed a flight-response measure may be taken by the UAV to prevent the UAV from flying in a no-fly zone. Different flight-response measures may be taken based on the distance between the UAV and the flight-restricted region and the rules of a jurisdiction within which the UAV falls.