Abstract: An integrated and mechanically aided warhead afterbody arming device for siles using mechanical rotation of the missile to arm the warhead is disclosed. A self-contained electrical generation system provides electrical power for the proper arming of the warhead. Mechanical rotation energy is used to generate electrical power for warhead arming. Revolution counters and mechanical detents are used to prevent premature arming.

Abstract: A hot gas control system includes a pressure vessel defining a chamber in which is disposed a body of solid propellant material that has a leading portion and a trailing portion. A first layer of the body of solid propellant material extends between the leading portion and an intermediate region of the body of solid propellant material, and a second layer extends between the intermediate region and the trailing portion of the body of solid propellant material. The first layer is composed of a first propellant composition that produces a relatively clean gas, and the second layer is composed of a second propellant composition that produces a relatively less clean gas.

Abstract: In a guided projectile such as a missile, it is often necessary to negate the lift force imparted by the wings (5) during early low velocity stages of flight. Thus, wings (5) can be flattened against the airframe (2) of the missile (1) by a passive constraint, e.g., a shrink tubing (35) which disintegrates due to aerodynamic heating at a higher velocity stage of the flight, allowing each wing (5) to deploy into a position generally orthogonal to the airframe (2). The deployment force can be provided by torsionally and compressionally preloaded springs (19).

Abstract: An open-ended diffusion chamber and an adjacent combustion chamber located in the nose of a projectile to receive ram air that ignites a solid fuel material within the combustion chamber. A pair of oppositely disposed lateral steering ports are provided aft of the combustion chamber and are interconnected therewith via a diverting valve that is controllable to selectively divert the escaping combustion gases from the combustion chamber to one or both of the steering ports to thereby change or maintain the trajectory course of the projectile after firing.

Abstract: In a guided moving warhead (1) which can be a missile or a projectile containing a long rod penetrator (3), alignment wings (5) keep the rod (3) in alignment with the warhead's velocity vector, thus maximizing its destructive potential. Two pairs of wings (5) are coupled to the rod (3) by means of a two-axis gimbal (7). One pair of wings (5) pivots along one axis of the gimbal (7) while another pair pivots about a second orthogonal axis. Aerodynamic forces cause the wings (5) to align with the relative wind, and as a result, the rod (3) aligns with the warhead's velocity vector as desired. Orthogonal components of crossflow acting upon the wings (5) can be compensated out by means of gearing the shafts (11, 15) which connect the wings (5) with the gimbal (7). In the case where warhead (1) is a missile, it is often necessary to negate the lift force imparted by the wings (5) during early low velocity stages of flight.

Abstract: 1. In a guiding and propulsion system for a missile, the combination which comprises:Communication means mounted in a central portion of the missile toward the aft end thereof and effective to receive and emit radiant energy along a rearward line of view substantially axial of the missile, to guide the missile, andNozzle means mounted on said aft end to propel the missile by generally rearward discharge of fluid, said nozzle means being canted outward from said central portion to keep said line of view free from said fluid.