Abstract: An attitude control system (ACS) for a spacecraft includes an attitude control assembly (ACA) interface, a control moment gyro (CMG) array and a reaction wheel assembly (RWA) control unit. The ACA interface converts torque commands received from the RWA control unit into CMG gimbal rates for the CMG array. The ACA interface receives CMG gimbal angles from the CMGs and converts the CMG gimbals angles into RWA speeds, which are then provided to the RWA control unit.

Abstract: An apparatus (10) comprises a first assembly (60) and a second assembly (62). The first assembly comprises a base (70) and an electrically energizable mechanism (108, 110), and has a first mounting portion (86). The second assembly (62) comprises an ignitable material (121) in a sealed container (120). The container (120) has a first wall portion (144) that is rupturable to enable ignition of the ignitable material (121). The container has a second wall portion (128) that is rupturable in response to ignition of the ignitable material (121) to enable flow of combustion products out of the container (120). The container (120) has a second mounting portion (152). The first mounting portion (86) of the first assembly (60) is in abutting engagement with the second mounting portion (152) of the second assembly (62) thereby to fix the first assembly for movement with the second assembly.

Abstract: A booster to relay a detonation train from a detonating cord to another booster includes an explosive and a shell. The shell has an open end to receive an end of the detonating cord and an indented closed end that is adapted to form a projectile to strike the other booster when the explosive detonates. The explosive may include at least fifty percent by weight of NONA, and in some embodiments, the explosive may be primarily NONA.

Abstract: A practice ammunition projectile comprises a head which bursts when the projectile strikes a target and contains a marking agent which optically indicates the point of impact after the head has burst. The marking agent consists of several chemical components (7, 8) which are each contained in separately breakable compartments (4, 5) within a burstable hood at the head of the projectile. When the compartments (4, 5) break open the components combine and undergo a chemical reaction which creates an optical mark. The hood is formed of an optically transparent material to enable the trajectory of the projectile to be tracked.

Abstract: The invention provides aerodynamic projectiles that include a projectile shell having an aerodynamic structure and a controlled center of gravity, which exhibit improved aerodynamics and resulting accuracy, and which are suitable for non-lethal uses. Methods of making such aerodynamic projectiles also are provided.

Abstract: A pair of mating components that are in very close quarters and which require essentially one-handed installation of a moveable part or component relative to a fixed part having mating linear wedge type ramps. The ramps on the moveable part will permit movement of the moveable part adjacent the fixed part, so that surfaces of the ramps on the movable part overlap ramps on the fixed part. Lateral movement of the moveable, part causes the ramp surfaces to engage to support the moveable part. The moveable part then can be clamped by further lateral movement so that the wedge type ramps urge the two parts to mate and seat.

Abstract: A person can safely descend from a burning high-rise building or the like using an inflatable flying body that has a hollow conical form in an inflated deployed condition, but is deflated and folded into a backpack form in a stowed condition. The flying body includes an upper stabilizing ring, a lower nose structure with a pneumatic damping body, spoke struts extending conically therebetween, a cover skin covering the abovementioned inflatable components to form the conical outer surface and provide aerodynamic braking drag, and gas generators to inflate the inflatable components. A person straps on the apparatus in the stowed backpack form and pulls a handle to actuate the gas generators for inflating the apparatus, whereby the expanding apparatus ejects the person from the building and then orients itself in a nose-down attitude during the descent. The pneumatic damping body damps and dissipates the landing impact energy.

Abstract: The invention provides a safety system for a small arms projectile in which an initiating device is impacted by a firing member in order to detonate a main explosive charge. The system requires the firing member to be retained in a safe position in relation to the initiating device by at least two independent mechanisms. The firing member is initially supported in a forward position, in which it assists in holding the initiator device in a safe condition, and is caused to move rearwardly, through inertia, when the projectile is fired, destroying one of the retaining mechanisms and allowing the initiator device to adopt a primed position in which it can be activated by the firing member which at this time is retained by the other retaining mechanism which is automatically released when the projectile is in flight.

Abstract: A kite in the shape of an aircraft having one or more wings. The number of wings can vary due to novel V-shaped connection members employed together with strut rod members cut to predetermined lengths. The connection members are preformed V-shaped connectors slidably mounted to spar members disposed in open-ended sleeves in the leading and trailing edges of a wing and may be oriented to receive strut members form either above or below the wing, for efficiency manufacturing, ease in assembly, and minimum exposure to breakage during operation, storage and transport. Additional connection members may be added to the spar members to receive strut members connected to additional wings thereby allowing for an airplane kite having one wing, two wings, three wings, or more. Multiple-V connectors may be combined to create hubs for propellers or wheels that rotate when they encounter a front wind. Ram air openings are utilized in the fuselage of the kite to maintain the shape of the fuselage and the angles of wings.

Abstract: The present invention provides a rocket engine (10) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine (10) includes a combustion chamber (12) having an injector end (14) and a nozzle end (16). A propellant injector (20) is in fluid communication between a propellant line and an inside periphery of the combustion chamber injector end (14). A nozzle throat (18) is formed at the nozzle end (14) of the combustion chamber (12). A nozzle exit cone (22) extends outwardly from the nozzle throat (18). A plug support (30) is coupled between a nozzle plug (28) and the propellant injector (20). The nozzle plug (28) aerodynamically self-compensates for changes in ambient backpressure at the nozzle exit cone (22) such that the nozzle thrust coefficient is maximized for any ambient backpressure.

Abstract: A pyrotechnic initiation delay device intended in particular to cooperate with a device for firing a pyrotechnic charge of the fuze type, particularly for a hand grenade, having a delay composition located inside a delay column, the latter having a lower end and an upper end, a percussion primer being able to cooperate with the upper part of the delay column, and a striker piston held firmly under the lower end of the delay column and able to move axially in the direction of the element to be struck under the action of an explosive charge cooperating with the lower end of the delay column. The delay column communicates with the explosive charge through a cavity containing plugging means allowing or preventing movement of the striker piston under the effect of the explosive charge.

Abstract: Described is a rudder blade mounting arrangement (10) for a missile comprising a rudder blade (12) and a mounting element (16) for the rudder blade. The rudder blade (12) is displaceable about a rudder blade axis member (36) of the mounting element (16) between a retracted inactive position and a deployed active position. The rudder blade foot (14) of the rudder blade (12) is connected in positively locking relationship to the rudder blade axis member (36) in such a way that, in the deployed active position of the rudder blade (12), the rudder blade foot (14) is forced against a front face (62) of a side portion (24) of the mounting element (16).

Abstract: This airlifting surface division idea provides for division of airlifting surfaces resulting in low induced and interference drag. It can be applied to aircraft wings and helicopter and windmill rotor blades to significantly reduce induced drag when compared to prior art. Also, it can be used for new concepts of large subsonic and hypersonic aircraft to significantly reduce their overall drag and external dimensions when compared to prior art, simultaneously providing for very good pitch maneuver and longitudinal stability of such aircraft.

Abstract: A pyrotechnic initiator with a narrowed sleeve attached to a header assembly and retaining a pyrotechnic charge, and methods of making same.

Abstract: An airborne glide slope tracking system includes a radio altimeter for producing a signal indicative of the instantaneous altitude of the aircraft and a glide slope error indicator for producing a signal indicative of the angular deviation from glide slope. The two signals are multiplied to produce a glide slope error signal in feet and fed to a summing device directly and through a lead filter to generate a signal for a throttle servo to increase or decrease the thrust of the aircraft. A longitudinal accelerometer signal is then added to a signal indicative of a difference between an aircraft's reference angle of attack and actual angle of attack to produce a signal to a pitch command to provide an angle which will be sustained by the power of the aircraft.

Abstract: An aircraft door has a trough substantially closed by an outer planking (21) except for a vent that vents the space enclosed by the trough and the planking to the atmosphere outside of the aircraft. The door also includes a door stiffening door framing that is preferably but not necessarily mounted inside the trough or between a radially inner wall of the trough and an inner door cladding or covering. The trough is formed by a radially inwardly recessed portion of the outer door skin.

Abstract: A security mount and system for protecting a firearm. The base of the firearm is placed in a receptacle in the mount to hold the firearm. A switch in the bottom of the receptacle is activated when the firearm is removed from the mount. The mount may be connected directly to an alarm or to a premises security system which sounds the alarm when the switch is activated. The premises security system may also report an alarm condition to a monitoring center via a wireline connection or a wireless link when the switch is activated.

Abstract: A fuze for a munition adapted to prevent unintended arming thereof. The fuze incorporates an arming screw having a keyed portion and a centrifugal locking mechanism for preventing rotation of the arming screw unless the fuze mechanism is in a rapidly spinning condition such as that experienced when the fuze and its associated munition are deployed from an airborne rocket or artillery shell, and thus spinning at a rate of at least several thousand rpm. The centrifugal locking mechanism includes a pair of locking members which are biased by biasing elements into engagement with the keyed portion of the arming screw. This prevents the arming screw from being accidentally unscrewed from an inertia weight within the fuze, thus placing the fuze in an unintended armed condition.

Abstract: The present invention is a light weight low profile variable shotgun bore choke that is easily manually adjusted by the user. To minimize the choke profile, the choke is connected to the shotgun through a threaded connection within the muzzle bore. External threads on a choke inner sleeve are configured to mate with standard threads found in existing prior shotgun barrel muzzles or with custom threads specifically formed. By using a threaded connection internal to the gun barrel, the overall radial dimensions of the choke are minimized thereby reducing the profile visible to the user. Weight is also reduced by a design which reduces radial dimensions and by use of light weight materials. The choke is adjusted by the user by manually rotating an outer adjustment sleeve with respect to an inner bore sleeve which is fixed to the shotgun barrel. The adjustment sleeve rotates through a range of choke conditions between two physical stops.

Abstract: An aircraft engine includes an exhaust gas purifying device for purifying exhaust gas from the engine, and a switching device for switching the engine between an emission-emphasized mode in which the exhaust gas from the engine is purified by the exhaust gas purifying device and an output-emphasized mode in which emphasis is placed on engine output.