差分流量调节推力矢量控制研究  

Investigation of Thrust Vector Control by Differential Throttling

作　　者：王一白[1] 刘宇[1] 王长辉[1] 覃粒子[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《宇航学报》2005年第1期112-115,共4页Journal of Astronautics

基　　金：国家863 2高技术航天领域[863 2 1 3 1]

摘　　要：为了了解差分流量调节实现推力矢量控制的特点,参考塞式喷管发动机XRS 2200的工作参数,对多单元直排型塞式喷管模型发动机进行了数值计算。介绍了差分流量调节的计算方法和内喷管与塞锥推力矢量变化的分析过程,计算产生的俯仰力矩。结果表明,差分流量调节时,塞式喷管轴向合力基本保持不变,不损失轴向推力性能;俯仰力矩包括轴向力和侧向力产生的两部分力矩,随差分流量调节增大而增加,有很好的偏转性能。结论可以为差分流量调节的实验研究提供参考。To know more about the characteristic of thrust vector control by differential throtding for aerospike nozzles, according to the parameters of XRS-2200, clustered linear aerospike nozzles were designed, analyzed and calculated by numerical simulation. The computing method of differential throttling and the analytical process of thrust vector of inner nozzle and plug were introduced. The generated moments of pitch were given. The results indicate that the variation of the axis thrust is a little through differential throttling, that the moments of pitch include two parts of moments generated by the axis thrust and the lateral force, and the moment of pitch is increased with augmenting differential throttling. The conclusions can provide valuable data for next experimental investigation of thrust vector control by differential throtding for aerospike nozzles.

关 键 词：推力矢量控制 差分流量 直排型塞式喷管 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]