Abstract: A simple, retractable, self-erecting wing for a low speed missile having a fabric wing cover affixed to a leading edge structure that is the only erected structural member in the wing operative position. The wing cover forms a pocket that contains air. The leading edge structure is hinged and folds, along with the wing cover, into a compact slotted space adjacent the outer wall of a missile body. In the folded position the leading edge structure forms a cover for the slot and the cover coincides with the outer shape of the missile body. A large fabric wing can be completely stored within the missile body for minimum drag during any high speed portion of the missile flight, the wing being released to the operative position by a simple mechanism.

Abstract: A novel composite armor for armored vehicles which attenuates mine blast loading better than monolithic steel armor plate of equal areal density without structural fracture. The disclosed composite armor, particularly used as vehicle floor armor, is designed so as to greatly enhance not only crew survivability, by markedly reduced compressive shock effect, but also vehicular integrity. The novel composite armor in most preferred embodiments comprises layers of high density steel honeycomb, balsa wood, and ballistic-resistant nylon such as KEVLAR, sandwiched in various arrangements between outer layers of steel armor plate.

Abstract: An articulated nose is locked in axial alignment with the longitudinal axis of a rolling projectile body. Pyrotechnic means within the nose is actuated to unlock the nose and tilt it toward the target when the error between the projectile path and the path to the target exceeds a predetermined threshold.

Abstract: A buffered bolt assembly is disclosed for use in an automatic weapon. A b is received in a sleeve on a bolt carrier and is movable therein both axially and rotationally. One or more cam pins on the bolt are received in respective cam guides in the sleeve to control the bolt's rotational position as a function of its axial position. The aft end of the bolt is provided with at least one and preferably two aftward-projecting bolt extensions, for which corresponding slots are provided in the aft surface of the sleeve. When the bolt carrier and bolt are in the battery or firing position, the bolt extensions protrude through their respective slots. The bolt extensions are of such a length that during the recoil stroke of the bolt assembly, the aft ends of the bolt extensions are flush with the rear outer surface of the aft wall of the sleeve.

Abstract: A combustion liner for a gas turbine engine operating at high temperatures has portions of the combustion liner double-walled, with a narrow clearance between the inner and outer walls through which cooling air flows to cool the liner. The surfaces of the walls which define these cooling air inlets are roughened to increase heat transfer from the air to the wall. The walls are joined and held apart by spacing strips extending axially of the liner and bonded to the overlapping wall sections. Large combustion air inlet holes extend through the overlapping wall sections at some points. Auxiliary air inlets for liner cooling are provided downstream of these combustion air inlet holes.

Abstract: A belt-fed automatic weapon includes a retainer for holding one or more of he leading rounds on the belt exposed external to the magazine in a position where they can be picked up and automatically fed into the automatic weapon by a feed sprocket in the automatic weapon during insertion of the magazine into the weapon. This permits one-hand loading by an erect walking operator whose second hand is occupied supporting the weapon. A belt guide at the exit of the magazine prevents jamming of linked rounds when the weapon is fired upside down or on its sides.

Abstract: A missile thrust vector control system using fixed valves and nozzles in n numbers, as 4 or 8, mounted so that the thrust vectors operate at preselected angles to the frame and are pulse modulated in certain combinations to produce thrust vectors the sums of which provide desired deflections in pitch, yaw, and roll, without altering axial propulsion thrust.

Abstract: A latching pin is held in a mating hole by a retaining wire prior to firing f a guided projectile to lock together a canard frame and an intermediate body which is part of a canard deflecting mechanism. Upon launch, the retaining wire is sheared by an inertia-driven shear mass but the latch pin is maintained in the latching condition by centrifugal force imparted to the canard frame and intermediate body during launch. Following launch, the canard frame and intermediate body are despun by aerodynamic drag on canards. Once despinning has proceeded sufficiently to reduce the centrifugal force to a value low enough to be overcome by a resilient member, the latch pin is withdrawn from the mating hole and relative rotation of the intermediate body and the canard frame are permitted to thus begin deflecting a pair of deflectable canards for producing aerodynamic lift to steer the projectile.