CAJ | 학술논문

对于药柱外/内径比(m数)很大的贴壁浇注式固体火箭发动机,在固化降温后,推进剂药柱内会产生显著的热应变,这严重限制了发动机的进一步高性能化. 加压固化是一种降低推进剂药柱内热应变的有效方法. 文中分析了加压固化的原理,推导出了加压固化所需压强与发动机参数之间的关系式,提出了一种两步分析法的加压固化有限元分析方法. 针对4种不同壳体材料的圆管发动机,进行了加压固化理论计算与有限元仿真分析,给出了4种壳体加压固化时的推荐压强.
대우약주외/내경비(m수)흔대적첩벽요주식고체화전발동궤,재고화강온후,추진제약주내회산생현저적열응변,저엄중한제료발동궤적진일보고성능화. 가압고화시일충강저추진제약주내열응변적유효방법. 문중분석료가압고화적원리,추도출료가압고화소수압강여발동궤삼수지간적관계식,제출료일충량보분석법적가압고화유한원분석방법. 침대4충불동각체재료적원관발동궤,진행료가압고화이론계산여유한원방진분석,급출료4충각체가압고화시적추천압강.
For those case-bonded casting solid rocket motors ( SRMs) with large outside/inside radius ratio of the grain, high thermal strain will be generated in the propellant grain subjected to thermal loading, which significantly limit the performance of SRM. Pressure cure is an effective method to reduce the thermal strain in the grain. In this paper, the theory of pressure cure was analyzed and the relationship between the desired pressure and the parameters of the SRM was deduced. Then, a finite element method ( FEM) of pressure cure named two step method was proposed. Theoretical calculation and FEM simulation were carried out on a tube motor with four different material cases. The recommended pressure of pressure cure of four cases were given out.