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为了获得固体燃料空气涡轮火箭发动机(SP-ATR)中涡轮和压气机的匹配工作特性,建立了涡轮和压气机的工作特性模型,根据SP-ATR转速、功率和背压平衡的工作特点,分别基于涡轮和压气机的工作环境先后采用两种不同的方法完成了二者的匹配。对比两种匹配方法得出结论:(1)基于涡轮的匹配方法与转速稳定过程一致,可确定特定飞行环境中发动机的转速;(2)基于压气机的匹配方法需要条件更少、适用范围更广,可用于特定转速调控方案下驱涡燃气流量的确定。两种匹配方法的计算结果相对Ax STREAM仿真结果的最大误差为10.75%,两种匹配方法的计算结果相差不超过8%。将建立的匹配方法应用于HARM弹自主爬升飞行过程,得到SP-ATR驱涡燃气流量的定量调控规律。
In order to obtain the matching performance of turbine and compressor in solid fuel air turbine rocket engine (SP-ATR), the operating characteristics of turbine and compressor are established. According to the working characteristics of SP-ATR speed, power and back pressure balance, Turbine and compressor based on the working environment has used two different methods to complete the match. Comparing the two matching methods, the conclusions are drawn as follows: (1) The turbine-based matching method is consistent with the speed stabilization process to determine the engine speed in a specific flight environment; (2) the compressor-based matching method requires fewer conditions and the applicable range is more Wide, can be used for the specific speed control program to determine the displacement of the gas flow. The maximum error of the results of the two matching methods with respect to the Ax STREAM simulation results is 10.75%. The difference between the two methods is no more than 8%. The established matching method is applied to the self-climbing flight process of HARM projectile, and the quantitative regulation rule of the SP-ATR displacement gas flow is obtained.