Abstract: A gun system comprising a recoiling cannon assembly, a stationary carriage having a cradle, and a campath and cam follower mechanism for moveably mounting the cannon assembly on the cradle for travel along a two-stage curvilinear recoil path. The first stage has a linear portion shaped to maintain prefiring orientation, and a curved portion with a decreasing radius of curvature in the direction of travel (i.e., recoil) to accelerate the cannon assembly upwards. The second stage, which may be straight or have a curved configuration different from that of the first stage, causes the cannon assembly's upward motion to be decelerated in a controlled manner. A recoil buffer assembly has deceleration characteristics matched in a predetermined relationship to the configuration of the curvilinear path, so that the instantaneous stabilizing moment of the reaction to the upward force of the recoiling cannon assembly and the moment of the static weight of the gun system.

Abstract: High velocity projectiles are able to continue in flight for considerable distances beyond the normal target range. The present invention is a projectile for use in practice firing which becomes unstable after the normal target range has been exceeded and comprises a training round (1) having a body portion (3) engageable with a sabot (4) for projection from a rifled gun barrel, and a tapered nose portion (2) protrusive beyond the sabot, which is provided with a nose tip portion (6) having spin fins (9) extending in planes radial to the longitudinal axis. The fins increase the rate of spin decay and cause instability of the round and the fin geometry is chosen such that the instability occurs when the target range has been exceeded. The finned nose tip portion is separable from the round so as to permit selective attachment of a nose tip portion having fins specifically dimensioned for terminating the trajectory at a chosen safety range.

Abstract: A construction for the delivery of propellant constituents to the main combustion chamber of a hypergolic liquid bipropellant rocket engine having a staged combustion cycle incorporating at least one precombustor comprises: a mixer for mixing together prior to delivery to the main combustion chamber a first propellant constituent comprising oxidant together with exhaust gas from the precombustor injector means for injecting the mixture of the oxidant and exhaust gas provided by the mixer into the main combustion chamber in such a manner that the injected mixture forms a recirculation zone inside the main combustion chamber, an inlet into the main combustion chamber for a second propellant constituent comprising fuel, and a delivery channel to the said inlet, the said inlet and delivery channel being disposed laterally of the injector means relative to the main direction of flow through the injector means in such a position that fuel delivered into the main combustion chamber thereby is delivered into the said