Abstract: This invention relates to a shock absorber for use with a command link controlled missile system. The shock absorber being designed to absorb the shocks produced by launch and missile movements and being particularly applicable to fibre optic command link systems.

Abstract: A projectile reaction control system includes a nozzle assembly in which the efflux exhausted thereby may be controlled in a continuously variable fashion. In one example control is by means of a slidable piston so that the thrust developed by the nozzle assembly is substantially linearly dependent on the displacement of the piston, whereby the reaction control system may be controlled by an autopilot with little or no modification.

Abstract: A thrust control valve which is operable to direct a gas supply to provide thrust is disclosed. The gas supply to obtained from a hot gas generator eg a rocket motor combustion chamber, and is directed through a nozzle by the operation of a plunger mounted within a pressure chamber. The pressure in the pressure chamber is controlled by the operation of a solenoid-operated poppet valve which moves between two positions to either pressurize the chamber ie sealing the nozzle with the plunger to provide no thrust, or to de-pressurize the chamber ie allowing gas from the gas supply to exit via the nozzle thereby providing thrust.