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导言空间发动机的工作压力比较低,喷管膨胀面积比较高。这种发动机大部份的研制工作是在海平面条件下用不带扩散喷管裙段的发动机进行的。根据海平面试验数据正确推断实际燃烧效率和精确预计实际真空推力系数,对满足系统研制要求是不可缺少的。为了用测量的推力而不用喷注器面的压力确定喷管滞止压力,并由此决定燃烧效率,从而确立了一种试验技
Introduction Space engine working pressure is relatively low, nozzle expansion area is relatively high. Much of this engine development has been done with engines without diffuser nozzle skirts at sea level. It is indispensable to meet the system development requirements by correctly inferring the actual combustion efficiency and accurately estimating the actual vacuum thrust coefficient based on the sea level test data. In order to determine the nozzle stagnation pressure with the measured thrust without the pressure of the injector surface and thus determine the combustion efficiency, an experimental technique