Abstract: The experiment system composing,design method of test motor,and experiment method are demonstrated.According to acquired data such as static temperature,static pressure and mass flow rate,analysis methods are put forward for the combustion efficiency,specific impulse efficiency.Without regard to the error during thmodynamic calculation,these parameters error are analyzed according to the current experiment system precision.It shows that the total pressure relative error is fairly higher with reduction from static pressure,static temperature and mass flow rate.This parameter should be tested directly.The relative errors of combustion efficiency,thrust gain specific impulse and bench force specific impulse are about ±3.6％.The main error sources are air mass flow rate,static pressure and bench force.Their accuracy should be controlled restrictively in order to reduce test errors. This paper provides the helpful references for ducted rocket experiment.

Key words: Ducted rocket；Connected-pipe experiment；Analysis method；Error spread

摘要： 阐述了固冲发动机直连试验和试验方法,并根据试验获得的静温/静压/流量等参数提出了试验分析方法,能够获得燃烧效率、比冲效率。在不考虑热力计算误差的条件下,根据试验系统的测试精度,对该方法进行误差分析,表明:(1)通过补燃室尾部静压、静温、流量来换算尾部总压,相对误差较大,应该对尾部总压进行直接测量。(2)用该系统得到的燃烧效率、推力增益比冲、台架推力比冲的相对误差在±3.6%左右,主要误差来源于空气流量、补燃室尾部静压、台架推力,应该对这些参数的测试精度进行严格控制,以减小试验误差。

关键词: 固冲发动机;直连试验;分析方法;误差传播