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轨道科学公司和美国空军研究实验室所属的军用太空飞机技术规划办公室共同获得了 NASA 马歇尔空间飞行中心(MSFC)上面级飞行试验(USFE)项目合同。轨道公司正在设计研制一种廉价的新型液体火箭,火箭采用压力供应系统,推力为4,540N(10,000磅),推进剂为 H_2O_2/JP-8。在 NASA Stennis 太空中心(SSC)进行的上面级飞行试验用燃烧室热试车时,当H_2O_2流量达到设计流量的1/3时,催化剂床发生了低频不稳定。本文介绍了上面级飞行试验催化剂床、燃烧室及其工作情况;讨论了催化剂床不稳定动力学;还介绍了用计算机动态模型模拟再现催化剂床的不稳定现象的情况。该计算模型建立在 SSC 试验数据的基础上,旨在探索解决催化剂床发生不稳定问题的可能方法。最后介绍了对催化剂床不稳定问题采取措施后,燃烧室的结构及其稳定工作情况。
Orbital Sciences and the Military Space Plane Technology Planning Office affiliated with the U.S. Air Force Research Laboratory have been awarded a contract with the NASA Marshall Space Flight Center (MSFC) Top Level Flight Test (USFE) project. Orbital is designing a new, low-cost liquid rocket using a pressurized supply of rockets at 4,540 N (10,000 pounds) and propellants H 2 O 2 / JP-8. At the NASA Stennis Space Center (SSC) in the upper flight test with a combustion chamber heat test, the catalyst bed developed low frequency instability when the H_2O_2 flow rate reached 1/3 of the designed flow rate. In this paper, the catalyst bed, the combustion chamber and the working conditions of the upper flight test are introduced. The instability kinetics of the catalyst bed is discussed. The instability of the catalyst bed is also simulated by the computer dynamic model. The calculation model is based on SSC test data and is intended to explore possible solutions to the problem of instability in the catalyst bed. Finally, the structure of the combustion chamber and its stable operation are introduced after measures are taken to deal with the instability of the catalyst bed.