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在某些运行导弹的级间分离过程中,已经观测出有大的不对称喷管流分离侧向力。由于在先进的运载火箭中采用了可延伸的喷管出口锥(ENEC),有效的级间分离空隙就很小了。因此,在导弹设计阶段,需要有一种可靠的喷管侧向力的预示方法。现有的方法都是依赖于无阻塞的喷管试验数据确定的。由于喷管受下面一级发动机前底的阻塞,用这些数据做级间分离分析是很不够的。本文介绍的经验方法,考虑到了喷管的阻塞问题,还将预示的结果同飞行试验和缩比模型试验的侧向力数据做了比较。
In some interstage separation of run missiles, it has been observed that there is a large asymmetric nozzle flow that separates lateral forces. Due to the use of an extendable nozzle exit cone (ENEC) in the advanced launch vehicle, the effective interstage separation gap is small. Therefore, at the missile design stage, there is a need for a reliable method of predicting nozzle lateral forces. The existing methods all rely on non-blocking nozzle test data. Because the nozzle is obstructed by the fore bottom of the next engine, it is not enough to do interstage separation with these data. The empirical approach presented in this paper takes into account nozzle blockage issues and also compares the results of the predictions with the lateral force data from the flight and scale model tests.