Abstract: A convertible multipurpose missile launcher includes a launch rail structure on the launcher body with a first-missile launch rail on the bottom side of the launcher body extending in a longitudinal direction. The first-missile launch rail is dimensioned for a first missile. A second-missile launch rail is positioned on the bottom side of the launcher body and extends in the longitudinal direction. The second-missile launch rail is dimensioned for a second missile different from the first missile. The second-missile launch rail includes a stationary second-missile forward launch rail segment, and a movable second-missile aft launch rail segment. The movable second-missile aft launch rail segment is slidable on the launcher body, and preferably on the first-missile launch rail, between a forward position and an aft position and may be locked in these positions.

Abstract: A method of packaging a multiplicity of infrared decoy foils into a canister having an aft end and a drive screw extending therein. The present method allows for the controlled dispensing and dispersal of the decoy foils from within the canister and comprises the initial step of assembling the decoy foils into at least one stack. The stack is advanced into the canister, with a preload being applied to at least a portion of the stack through the use of at least one separator plate cooperatively engaged to the drive screw. The preload applied to the decoy foils is of a force greater than or equal to that required to dispense the decoy foils from the canister.

Abstract: A pneumatic actuator operable to carry a missile on an aircraft and to eject the missile from the aircraft in flight on demand, includes a differential area piston which is slidable in a closed chamber which is filed with air under pressure. The smaller diameter portion of the piston is slidably engaged in a cavity which is formed in an end wall of the closed chamber. An actuating rod extends co-axially from the smaller diameter piston portion out of the closed chamber. Initial movement of the piston to actuate ejection of the missile is effected under low force by the application of pressure to the end of the smaller diameter piston portion remote from the larger diameter piston portion until the smaller diameter portion is displaced from the cavity into the closed chamber which allows the largest possible force to be exerted on the piston by the action of the compressed air on the larger diameter piston portion.

Abstract: A payload dispensing system for an aircraft is disclosed that includes a housing mounted to the aircraft. A hollow shaft is mounted to the housing having an open first end and a closed off second end with a hole therethrough. The payload includes an aperture having a first end on an external surface thereof and a second end in the interior therein. A wire cable releasably secures the payload to the housing such that the hollow shaft extends into the aperture of the payload. A compression spring is mounted at least partially within the hollow shaft, having a first end in contact with the second end of the hollow shaft and a second end in contact with the second end of the aperture within the payload, the spring having a compressed position when the hollow shaft is within the aperture in the payload and asserts a force tending to separate the payload from the aircraft.

Abstract: A target penetrating aerial bomb including a penetrating body shaped for improved target penetration, having a narrower impact profile at approximately the same weight as an existing bomb. An aerodynamic shroud encases the penetrating body and emulates the aerodynamic shape of the existing bomb, and the weight, center of gravity, and moments of inertia of the bomb closely approximate those properties of the existing bomb. The bomb constructed according to the present invention may be qualified by similarity to the existing bomb, thus avoiding lengthy and costly qualification procedures.

Abstract: An automatic and sequencing pneumatic actuation assembly is provided for use in an ejection system capable of unlocking and forcibly ejecting stores from racks mounted on an aircraft or similar weapon carrier. The actuation assembly including a primary valve and release ram for reciprocating movement along a common longitudinal axis between closed and open positions. A solenoid control valve initiates movement of the primary valve by creating a pressure imbalance across the primary valve. Pressurized gas is caused to vent to an environment having a pressure lower than the pressurized gas, allowing the primary valve to move the release ram into engagement with a mechanism capable of unlocking the hooks before moving ejector pistons to forcibly eject the unlocked stores. A bias member is provided for automatically returning the primary valve to the closed position after the stores have been released.

Abstract: An air-dropped ammunition includes an ammunition body having a rearward portion; a firing pin accommodated in the rearward portion; a stabilizing band being received in a folded state at least partially in the rearward portion of the ammunition body; and a device for securing the stabilizing band to the firing pin. The device includes a disk having an upturned rim. The disk engages face-to-face one of two overlapping ends of the stabilizing band, and the upturned rim is oriented away from the overlapping ends. The overlapping ends and the disk are firmly attached to the firing pin.

Abstract: A compact universal apparatus which is mountable within an optimally sized weapons bay of a conventional fighter aircraft, which includes an automatic scissors or trapeze type lowering linkage mechanism for a conventional or inventory bomb ejector rack unit (BRU) having automatic latching, release and forced ejection mechanisms for conventional inventory weapons, characterized by an adaptor designed for the fixed attachment of the bomb ejector rack unit to the linkage of the lowering mechanism of the apparatus. The ejector rack unit is one adapted to the forced ejection of large bombs, attached or latched directly thereto, and to the rail launching of missiles having launching rails attached or latched directly to the ejector rack unit, with conventional automatic latch up of the bail lugs of the bombs to the launch rack lugs of the ejector rack unit, for forced ejection of the bombs, and with conventional automatic latch up of launch rails of conventional missiles for rail launching of the missiles.

Abstract: A universal warhead adapter comprises a tubular sleeve configured to contain any of various warheads of different configurations, and an aft bulkhead designed to replicate the aft end of a standard warhead with which existing tail assemblies are compatible. A universal missile is made by disposing a selected warhead within the sleeve and fixing the warhead therein with fastening mechanisms, and attaching a tail assembly to the aft bulkhead and a nose assembly to the forward end of the sleeve. Control surfaces, rocket motors, and/or turbine engines can be attached directly to the sleeve. An umbilical can be routed internally from a tail assembly through the sleeve and can be connected to an aircraft electrical system via an integral connector attached to the sleeve.

Abstract: An adaptor for releasably attaching a store to a rack on the underside of an aircraft. The rack has at least one hook connected to the rack and pivotable between a closed position for retaining the store on the rack and an open position for installation of the store on the rack and release of the store from the aircraft. The adaptor has a generally continuous lower surface shaped to conform to the outer surface of the store, an upper surface, and a surrounding wall connecting the upper and lower surfaces. The upper surface has a post extending downwardly from the rack for stabilizing the store against longitudinal and lateral movement of the store relative to the rack due to air loads during flight. The surrounding wall has a least one recess formed therein for receiving the hook. The adaptor is shaped so that upon release of the store, aerodynamic drag resulting from the presence of the adaptor on the store is minimized.

Abstract: A specially designed support structure is used to mount a pair of conventional elongated bomb racks, each adapted to releasably support either a missile or a torpedo, on the underside of a helicopter on opposite sides of its longitudinal centerline, with the lengths of the bomb racks extending parallel to the centerline. The support structure includes a pair of reinforcing plates secured to vertical sides of longitudinally extending keel beams on opposite sides of the centerline. Each plate has front and rear bottom mounting lugs that extend downwardly through corresponding openings in the helicopter underside. The front and rear mounting lug pairs are respectively connected to opposite ends of front and rear cross beam members, which longitudinally extend transversely to the centerline, by adapter structures that also support opposite end portions of the bomb racks.