固体火箭发动机反向喷管推力终止技术

本文讨论了打开反向喷管时推力终止过程的燃烧室压力衰减和推力瞬变的计算方法。对理论计算与试验结果进行比较,表明经过修正的理论计算结果与试验结果符合得较好。 

TECHNIQUE OF THRUST TERMINATION WITH REVERSAL NOZZLE FOR SOLID ROCKET MOTORS

This paper presents a discussion of the calculation approach to the pressure decay in the motor chamber and thrust transient,as a result of the blowing-out plug of reversal nozzles during the thrust termination process of the solid rocket motor. The delay time in the blowing-out process and correction to the exhaust coefficient Cw under the chamber pressure less than 2500 kPa is considered in the calculation of pressure decay. The transient thrust is calculated by use of the variation of thrust coefficient both in main nozzle and reversal nozzle with the chamber pressure. The tailoff impulse is calculated with integration. A comparison of theoretical calculation with testing results shows that the corrected theoretical calculation approach agrees well with the testing results.