Solid fuel rocket propulsion system - has braking force determined by difference between thrust jet outlet pressure and atmospheric pressure

摘要

The rear end of the propulsion nozzle terminates as a deflector ring with a turbine blade shaped cross section. The gases can be turned at an angle of 180 deg. to give a braking effect. The apparatus is designed to minimise the height reached by a meterological rocket by increasing the braking effect of the deflector ring at high altitude. The deflector ring is fixed and there is a gap between it and the end of the propulsion nozzle. The gases from the rocket are not fully expanded in the propulsion nozzle. As the rocket gains height, this condition becomes more acute, and the high speed jet expands until its edges enter the deflector ring and are turned through 180 deg.