Abstract: The present invention relates to weapon systems that accelerate projectiles using gases generated by the rapid combustion of a solid propellant, in particular, such a weapon system is able to vary the barrel exiting velocity of the projectile through a barrel venting means. In one embodiment, a front venting means exhausts gas generated by combusting propellant from behind the accelerating projectile and redirects a portion of the exhausted gas either to at least one fixed volume, to the front of the projectile, or to a combination of at least one fixed volume and to the front of the projectile. Redirecting some of the exhausted gas to the front of the projectile restrains the projectile, thereby slowing the projectile, and thus further decreasing the muzzle velocity of the projectile. In another embodiment, gas from behind the projectile is exhausted into a fixed volume, thereby decreasing projectile acceleration, and thus, the muzzle velocity of the projectile.

Abstract: The present invention is directed to a unique foldable winglet assembly adaptable for use with an aircraft for maximizing the wing span of the aircraft during cruise operation while reducing wing bending moment during extreme flight maneuvers. A foldable winglet is pivotally joined to the aircraft wing and is rotatable during flight between a retracted position and a fully extended position. An actuator is mounted on the aircraft wing and attached to the foldable winglet. When the aircraft reaches cruise operation, the actuator can be manually or automatically energized to pivot the winglet from a substantially vertical, retracted position to a fully extended position wherein the winglet becomes an extension of the wing. During cruise, the wing and winglet form an enlarged wing that serves to maximize lift of the aircraft.

Abstract: A system and method for determining the angular orientation of a body moving in object space. The invention is usable to detect and identify the angular orientation of the body relative to the theoretical plane of gravity and thereby relative to any other theoretical plane between zero and three-hundred sixty degrees therefrom. The invention is operable regardless of whether the body is rotating with an angular velocity, either natural and/or induced. The invention may employ one or more analog and/or digital sensors. The analog sensor may be an accelerometer. The system may be used to provide real-time orientation data to permit the body to be guided or directed towards a desired destination or simply to permit the orientation of the body to be known, controlled or varied as desired.

Abstract: A separation system for separating a first section from a second section is disclosed. In one embodiment, the separation system includes first and second doublers for initially interconnecting the first and second sections, an expandable explosive system contained in a cavity defined by the first and second doublers and first and second sections, and a slide plane including first and second slide members, the first and second slide members slidably engagable with each other for at least initially guiding the first section away from and relative to the second section upon severance of the first and second doublers.

Abstract: An aircraft locking system (11) is provided that avoids inadvertent or deliberate operation of an aircraft exit opening means (50) during take-off roll, in-flight, or during landing. The aircraft locking system includes means for determining whether engines of the aircraft are running (12), means for determining thrust lever position (14), means for determining whether the aircraft is in an air mode or a ground mode (16), and means for determining whether a predetermined number of service/entry doors are closed (18). Means for generating a lock/unlock signal (32, 40) are responsive to the engine running determining means, the thrust lever position determining means, and the service/entry door-closed determining means.

Abstract: Contactless data transfer devices are provided as an interface for the digital data transfer between a missile and a launcher in which the missile is accomodated.

Abstract: A spacecraft structure using functionally independent modules assembled around a lightweight core structure to provide a vehicle that is lighter, uses less volume, and is easier to design, manufacture and test than a conventional spacecraft. In the disclosed embodiments, the modules are formed on generally flat panels, which serve as thermal radiators. The modules extend radially from the core structure and are attached to the core structure either in coplanar rows that extend axially along the core structure or in a coplanar set that extends circumferentially around the core structure. Interconnection between modules is achieved through a backbone interface, through which the modules are connected to the core structure. A large number of variant configurations may be implemented using the modular approach, by selecting a core, components and modules of number and size to meet mission requirements.

Abstract: An apparatus for and method of detonating unexploded mines is disclosed. A ground-engaging foot is caused to reciprocate by power means with sufficient force to activate an unexploded mine. Control means is used to control the manner of reciprocation of the foot by controlling the power applied to the foot. A shock absorption arrangement absorbs shock energy created upon detonation of an unexploding mine. Preferably the apparatus is vehicle mounted for example upon a remotely controlled tracked vehicle.

Abstract: A launch vehicle mounting system for use in launching either of first and second launch vehicles having different booster diameters is disclosed. In one embodiment, the launch vehicle mounting system includes a mounting frame and a plurality of arms pivotally interconnectable to the mounting frame for supporting either of the first and second launch vehicles positionable thereon. In particular, the launch vehicle mounting system of the present invention is adapted to support either the first or the second launch vehicle as the arms are at least radially adjustable relative to the mounting frame to at least first and second radial positions corresponding to the booster diameters of the first and second launch vehicles.

Abstract: A vane control system (2) for a guided missile (1) with at least two vanes (3) has two toothed rings (7, 8), which are arranged in parallel to one another on both sides of the vane axes (18), are driven by pinions (15, 16) which are driven by electric motors and rotate continuously. Two drive gears (11, 17), which engage one of the toothed rings (7, 8) and rotate together with them such that they have opposite directions of rotation, are arranged on each vane axis (18). A clutch disk (19), which can be connected to one of the drive gears (11, 17), as a result of which the vanes (3) can be rotated in the desired direction, is arranged between the drive gears (11, 17). A brake (22) for fixing the vane axis (18) and an incremental transducer (23) for indicating the actual position of the vane are arranged on each vane axis (18).

Abstract: A system (10') for generating a missile guidance gain factor adapted for use with guided missiles. The inventive system includes a guidance control system (52) for obtaining current guidance parameters(55, 57) including ideal navigation gain, closing rate, line of sight rate, missile maneuverability, and missile velocity parameters. Software (56) running on a guidance control processor (54) computes a current guidance gain factor reflective of the current maneuverability of the missile from the guidance parameters (55, 57). In the illustrative embodiment, the system 10' further includes a nonlinear notch circuit (56) that generates an acceleration command (59) from the guidance parameters (55, 57) that varies in response to varying missile maneuverability parameters (57). The guidance control system (10') includes a conventional guidance law computation circuit (54, 55) and electromagnetic sensing equipment (52).

Abstract: A variable configuration final nozzle assembly for a combined rocket/ramjet engine consists of a fixed annular plug 20 together with upstream and downstream arrays of flaps 10,14 pivoted to the wall of a jet pipe 1 at their upstream and downstream ends 12,16 respectively. In the rocket mode of operation the upstream and downstream flaps are pivoted inwardly and locked in contact with the annular plug to form convergent and divergent portions 2,4 of a nozzle for the rocket exhaust which passes through the plug where a nozzle throat is defined by the internal surface of the plug. In the ramjet mode of operation the flaps lie alongside the jet pipe wall and ramjet exhaust gas flows through and around the plug. A second throat 50 is defined for the flow through the annular nozzle surrounding the plug and flow conditions in both parts of the flow are matched.

Abstract: To combat the formation of ice on an aerofoil, several resistive elements each consisting of electrically conducting fibers parallel to the leading edge and through which an electric current is made to flow to dissipate heat by a Joule effect are incorporated into this aerofoil close to its leading edge. In order to obtain a thermal power which can vary along the leading edge, the resistive elements are produced by superposing several layers of conducting fibers, at least one of which layers has a constant width, and at least one other of which has a width which varies continuously along the leading edge, but remains smaller than said constant width.

Abstract: A firearm cartridge case capable of withstanding internal gas pressures of at least about 50,000 psi has two substantially cylindrical portions of significantly different diameters interconnected by a frusto-conical shoulder portion. The case has a ratio of its overall length to its diameter, at a location 1.25 inches from its base, of no more than about 4.2, giving it an unusually short, fat profile. The base of the case has a rim with an outer diameter substantially no less than the case diameter at the aforementioned location, to facilitate reliable feeding of the cartridge from the magazine. The corresponding firearm chamber which matingly accepts the cartridge is capable of withstanding internal gas pressures of at least about 65,000 psi.

Abstract: An amphibious water bomber float plane, wherein the water bomber plane is equipped with a pair of floats for landing and taking off on water, with wheels for use on land, and having pair of floats secured for supporting the plane on water, water tanks within the floats for accumulating water for water bombing, scoops mounted in each float for lowering and raising between lowered and raised positions, and, when in the lowered position, the scoops entering the surface of the water causing water to flow upwardly into the tanks, dump doors mounted in each float, in communication with the tanks, the dump doors being swingable between an open dumping position and a closed sealed position, and controls by which the dump doors may be operated from the plane. Also disclosed is a method of water bombing from an amphibious float plane.

Abstract: A gimballed camera (34) is attached to a moving body (20) so that it can remain pointed at a desired target (28) as the body (20) moves. A gyroscope (38) is attached to the camera (34) so that it may move independently from the camera (34), so that the gyroscope (38) continuously points in one direction while the camera (34) moves relative to the gyroscope (38). Measurement devices determine the positions of the moving body (20) and gyroscope (38) relative to the camera (34). The sum of these measures yields the position of the target relative to the gyroscope (38), which translates to a command to point the gyroscope (38) at the target. The camera (34) is then moved independently to a specified alignment relative to the gyroscope (38).

Abstract: A separation system for separating a first section from a second section is disclosed. In one embodiment, the separation system includes first and second doublers for initially interconnecting the first and second sections, an expandable explosive system contained in a cavity defined by the first and second doublers and first and second sections, first and second grooves positioned on the first and second doublers, the first and second doublers severable along break planes defined by the first and second grooves, and bend augmenters associated with at least one of the first and second doublers to facilitate hinging of the doubler upon firing of the explosive, which thereby reduces separation shock.

Abstract: An infrared seeker head for a missile includes a viewing lens system and a focal plane array on which the visual field of the lens system is focussed. The image acquired by the focal plane array is displayed on a video display unit. Mounted on the missile launch tube in the beam path of the seeker head viewing lens system is a wide angle lens, which can be retracted to remove it from the seeker head beam path. The wide angle lens enables the gunner to view a large visual field initially. Then, when a "suspicious" object is detected, it can be removed to allow a positive identification of the type of target. A pair of rotating optical wedges are disposed in the beam path of the seeker head, so that its relatively smaller visual field can be diverted to compensate for maneuvering of the target.

Abstract: A suspension lug system for use with a jettisonable weapon that provides a mechanical interface between the weapon and a multiplicity of aircraft. The system has a dual-function lug that is disposed in a well when it is in a stowed position, and that is pivotable in opposite directions on a transverse pivot pin. A first end of the lug is configured as a saddle lug that is exposed above the outer surface when the lug is rotated into a saddle-deployed position. The second end of the lug is configured as a clevis that is exposed above an outer surface of the system when the lug is rotated into a clevis-deployed position. A spring is coupled to the lug that spring loads it and returns it to a stowed position when it is not engaged with the ejector release unit to preserve the outer contour of the weapon.

Abstract: An aerodynamic control system for an aircraft comprises a pair of low-aspect-ratio strakes integral with the fuselage, each of the strakes being substantially co-planar with an associated one of the wings and extending between a leading region generally blended with the trailing edge of the wing, a trailing edge and an outer edge. An aft airfoil is pivotally mounted to the trailing edge of each of the strakes movable between an extreme positive angle of attack position and an extreme negative angle of attack position. The aft airfoil includes an inner airfoil member which is laterally coextensive with said trailing edge of said associated strake and an outer airfoil member integral with the inner airfoil member which extends laterally beyond the outer edge of the associated strake. In one embodiment, the outer and inner airfoil members are substantially co-planar. In other embodiments, the outer airfoil member may be canted either upwardly or downwardly with respect to the inner airfoil member.