RBCC火箭引射模态热力壅塞研究

吕翔; 何国强; 刘佩进; 李宇飞

RBCC火箭引射模态热力壅塞研究

西北工业大学航天学院, 西安 710072

基金项目: 国家863计划项目

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出版历程
- 收稿日期: 2007-02-06
- 修回日期: 2007-09-17
- 刊出日期: 2008-03-28

An investigation of thermal choke in rocket ejector mode

School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 运用理论分析和实验研究相结合的方法对火箭引射模态下实现热力壅塞进行了研究.建立了用于实现热力壅塞可行性分析的理论模型,分析了燃烧室通道面积变化规律、加热方案、一次火箭与二次流掺混后的气流参数等对实现热力壅塞的影响,提出了判别能否实现热力壅塞的临界马赫数准则.理论计算和实验研究结果表明,碳氢燃料发动机在地面静止状态下难以实现热力壅塞,在一定飞行状态下可以实现热力壅塞.通过地面直连实验实现了来流马赫数为1.2条件下的热力壅塞及其主动控制,壅塞位置的调节范围达到了燃烧室长度的1/4.
- 航空、航天推进系统 /
- 火箭基组合循环 /
- 火箭引射模态 /
- 热力壅塞
Abstract: Thermal choke active control in rocket ejector mode and ramjet mode was investigated theoretically and experimentally for the integral design of RBCCengine.Theoretic model for possibility analysis of realizing thermal choke was set up.The effect of combustor geometry,heat adding scheme,flow parameters of the primary and secondary mixture on thermal choke was analyzed.Aprinciple of critical Mach number for determining the possibility of reaching thermal choke was proposed.Both theoretical results and experimental results show that it's difficult to reach thermal choke at sea level static for HC-fueled RBCCengine,while it becomes more easily under some flight conditions.Thermal choke with active control was achieved under the flight Mach number 1.2 on the direct-connecting test facilities of NWPU,with the adjustable range up to one quarter of the combustor length.
- aerospace propulsion system /
- rocket based combined cycle(RBCC) /
- rocket ejector mode /
- thermal choke

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参考文献(9)

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