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: A launch tube (2) for launching a missile (4) is supported by a single base (6) which enables the tube (2) to pivot about orthogonal yaw and pitch axes. An aerodynamic stabilizing trim tab (20) is positioned within the interior rear of the launch tube (2). During launch, exhaust gases from the missile (4) flow over the trim tab (20), producing a lift torque which balances the torque about the pitch axis caused by gravity acting upon the missile (4). This gravitational torque would otherwise tend to pull the nose of the launch tube (2) increasingly downward as the missile (4) is launched. The angle of incidence of the trim tab (20), its surface area, and its distance from the pitch axis are varied to adjust the lift torque and the drag attributable to the trim tab (20). The drag is used to balance forward frictional force upon the launch tube (2) caused by the motion of the missile (4). The pitch torques and the linear forces are balanced simultaneously.