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运载火箭级间热分离过程中,级间段受高温高压喷流的影响,所处环境恶劣,研究级间热环境中压力、温度和热流分布规律对级间段结构的优化具有重要意义。在Φ1m高超声速风洞中,采用以微型固体火箭燃气为喷流介质的热喷流模拟技术,模拟了运载火箭二级主发动机和四个游动发动机同时工作多喷流干扰条件下的级间热环境,并对级间压力、温度和热流测量试验技术进行了研究,获得了不同级间距、不同排燃窗开口数量情况下的二级底封头和一级前封头表面的热流、温度及压力分布特性。试验结果表明,级间距越小,分离环境越恶劣,压力、温度、热流分布越不均匀;总排燃面积保持不变,排燃窗开口数量变化,对一级前封头上的压力、温度、热流影响不大,但对二级底封头影响较为明显,随着开口数量的减少,二级底封头上压力、温度、热流值均有所增大。本项试验采用同轴热电偶测量了级间区域的热流,热流结果精准度的提高以及热流模拟准则还需进一步探索和研究。
In the course of thermal separation of carrier rocket stages, the interstage section is affected by the high temperature and high pressure jet flow, and the environment is bad. It is of great significance to study the distribution of pressure, temperature and heat flux in the interstage thermal environment for the optimization of the interstage structure. In the Φ1m hypersonic wind tunnel, the thermal jet simulation technology using micro-solid rocket gas as the jet medium was used to simulate the interstage between the two main engines of the launch vehicle and the four jet engines working under the condition of multiple jet interference Thermal environment, and the inter-stage pressure, temperature and heat flow measurement test techniques were studied to obtain the different levels of spacing, different openings of the number of openings in the case of the second end of the first end of the first sealing head and the surface heat flow, temperature And pressure distribution characteristics. The results show that the smaller the inter-stage distance, the worse the separation environment, the more uneven the distribution of pressure, temperature and heat flux; the total area of combustion remains unchanged and the number of openings in the exhaust window changes. The pressure, temperature However, the effect of heat flux is not significant, but the effect on the secondary end cap is more obvious. With the decrease of the number of openings, the pressure, temperature and heat flux on the secondary end cap increase. In this experiment, the coaxial thermocouple was used to measure the heat flow in the interstage region. The accuracy of the heat flow and the heat flow simulation criterion need to be further explored and studied.