关键词: 液体火箭发动机；燃烧室；壁面热流；壁面温度；燃烧室压力

Abstract: To study the thermal loading of the liquid rocket engine combustion chamber wall，a simple and accurate method to measure the heat flux of the combustion chamber wall was proposed. Combustion chamber transient temperature data in different radial depths were obtained by conducting rocket engine hot-test. Then，a method of processing data，which was based on the separation of variables，was applied to acquiring the heat flux and temperature of the combustion chamber wall. The conclusions of the research are as followed. The method used in this paper can measure the heat flux and the temperature of combustion chamber wall accurately and will not enlarge the error. During the transient process of the engine hot-test，the response of the combustion chamber wall temperature has obvious hysteresis and 5 seconds are not long enough for temperature to reach the steady state. However，the time that wall heat flux required to reach the steady state is about 2 seconds because of the rapid response，and the changing process of the wall heat flux is similar with the changing process of pressure.

Key words: Liquid rocket engine；Combustion chamber；Wall heat flux；Wall temperature；Combustion chamber pressure