轨/姿控发动机脉冲后效冲量快速算法的研究及应用  

Research and application of fast algorithm for pulse residual impulse of divert and attitude control engine

作　　者：张伟[1] 陈锋[1] 马军强[1] 刘帅[1] 

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《火箭推进》2012年第1期51-56,共6页Journal of Rocket Propulsion

摘　　要：轨/姿控发动机脉冲性能需在地面高空模拟试验中进行考核,试验数据需即时提供,针对脉冲后效冲量的计算,当前方法不能兼顾速率和统计偏差。简述了后效冲量计算要求、高模试验特点、Pacific6000原理及数据文件结构。在分析当前计算方法优缺点基础上,将网络脚本语言的设计思想引入试验数据处理过程,提出了实现数据快速处理的数据流式算法,基于此算法开发了工程应用软件,在实际试验中应用,取得了良好效果。Performance of divert and attitude control engine with pulse work mode must be checked in the altitude simulation test on the ground. The test data should be provided immediately. As for the calculation of the pulse residual impulse, the current way cannot keep balance in velocity and statistic deviation. The requirements of pulse residual impulse calculation, characteristics of alti- tude simulation test, principle and data file format of Pacific6000 are illustrated. On the basis of ana- lyzing the advantages and disadvantages of the current algorithm, a data flow algorithm for data fast processing is proposed by introducing the network script langue design idea into the testing data pro- cessing. The engineering application software was developed based on the algorithm and applied in the real tests successfully. This algorithm has an important reference significance for similar calcula- tion and mass data processing.

关 键 词：轨/姿控发动机 高空模拟试验 脉冲工作模式 后效冲量 快速计算 

分 类 号：V430-34[航空宇航科学与技术—航空宇航推进理论与工程]