CONTOUR DESIGN FOR SOLID-PROPELLANT ROCKET-ENGINE NOZZLE

Tóm tắt

In this paper, the characteristic line method is used to establish the equation describing the nozzle diverging contour. The converging contour of the nozzle is built according to the Witoszynski formula. Numerical calculation is applied to the 9M22Y uncontrolled rocket. The new nozzle design length reduced by 27.50%; the maximum thrust increased by 1.96% compared to the initial nozzle. The results in this paper are given parameters of the new nozzle having more optimal than the original nozzle. This result can be used to increase the range of 9M22Y rocket in particular and other missiles in general.