一种固体火箭发动机性能仿真与评估方法研究  

New Method for SRM Performance Simulation and Assessment

作　　者：孙勇强[1] 蔡强[1] 鲍福廷[1] 刘旸[1] 

机构地区：[1]西北工业大学航天学院

出　　处：《计算机仿真》2012年第4期55-59,共5页Computer Simulation

基　　金：国家自然科学基金(51005179)项目资助

摘　　要：关于固体火箭发动机性能的准确评估问题,针对固体火箭发动机试验耗费时间周期长,且评估性能决定动力系统的可靠性。发动机在工作过程中的推力、燃烧室压强、总冲量、比冲量等性能参数的可靠性均存在一个置信区间,通过试验方法难以评估在制造及使用过程中的随机因素影响下的性能可靠性。可用蒙特卡洛仿真方法解决上述问题。为了更全面评估性能参数的可靠度,引入了抽样验收方法,得到了性能参数可靠度的置信区间。采用修正内弹道计算模型,对大扩张比发动机进行仿真,结果与试验数据进行了对比。实验表明,仿真模型的精确性可以满足要求,结果与试验数据具有较高的一致性。证明评估方法可以全面的反应性能参数的统计特性,可为发动机的可靠性提供保证。SRM tests are costly and time consuming,and system reliability is base on the performance.Reliabilities of SRM performance such as thrust,combustion chamber pressure,total impulse and specific impulse have some confidence intervals.It is difficult to assess the distributed characteristics and reliability of SRM performance only by tests.Monte Carlo simulation method was used to solve this problem.To assess the reliability of SRM performance reliability comprehensively,acceptance sampling was introduced to confirm the reliability confidence interval.Acorrection interior ballistics model was used to calculate large area expansion SRM performance.Finally,compared with test results,the simulation model is accurate and the simulation result is in a good agreement.Statistical properties of SRM performance are better reflected by use of new method.

关 键 词：固体火箭发动机 蒙特卡洛 性能仿真 内弹道 

分 类 号：V448.153[航空宇航科学与技术—飞行器设计]