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液体火箭发动机试验推力测量的准确性对评价发动机性能意义重大。为减小1 200 k N液氧/煤油发动机地面试验时由于试验系统的原因对发动机推力测量准确性带来的影响和提高推力测量精度,针对1 200 k N液氧/煤油发动机试验台的推力测量系统,通过理论分析和试验验证的方法分析了泵前管道推力分离面上的2台波纹管的受力状态及波纹管在低温状态和受压状态下对推力测量的影响,获得了波纹管的竖向推力损失、低温与常温推力原位校准斜率修正系数、负推力修正系数等重要数据,并提出了波纹管安装固定要求,为修正1 200 k N液氧/煤油发动机推力测量数据、提高发动机推力测量准确性提供依据。
The accuracy of the liquid rocket engine test thrust measurement is of great significance for evaluating engine performance. To reduce the impact on the thrust measurement accuracy of the engine due to the test system at ground tests of 1 200 kN liquid oxygen / kerosene engines and improve thrust measurement accuracy, the thrust against a 1 200 kN liquid oxygen / kerosene engine test stand Measuring system, through theoretical analysis and experimental verification method, the stress state of the two bellows on the separating surface of the pipe before the pump and the influence of the bellows on the thrust measurement under the condition of low temperature and pressure are analyzed, and the bellows Vertical thrust loss, low temperature and normal temperature in situ calibration slope correction coefficient of thrust, negative thrust correction coefficient and other important data, and put forward the requirements of corrugated pipe installation and fixing, in order to amend the 1 200 kN LO / kerosene engine thrust measurement data to improve Engine thrust measurement accuracy to provide the basis.