作　　者： ; ; ; ; ;

机构地区： 西安交通大学能源与动力工程学院

出　　处： 《西安交通大学学报》 2003年第3期321-324,共4页

摘　　要： 为了考核贮存××年的液体火箭发动机的性能 ,进行了液体火箭发动机热试车的研究 .实验采用了NEFF62 0实时全数字采集系统 ,得到了在启动段、平稳段、关机段燃烧室的压力、推力、推进剂流量及压调器、稳定器出口压力等主要参数随时间变化的曲线 .对实验结果分析表明 :3次热试车数据在启动段都具有很好的一致性 ,贮存××年后的发动机仍具有良好的启动特性 ;关机段各参数的特征变化曲线非常接近 ,各参数在得到予令关机信号后都能迅速转入末级工作状态 ,并存在明显的“平台”效应 ,仍然具有良好的运载精度 ;压调器和稳定器都具有很好的调节性能 ,能满足发动机正常工作状态下的要求 .得出的结论对发动机的性能考核、设计。 To examine the performance characteristics of liquid rocket engine (LRE) which has been stored for certain years, the experimental investigation is conducted using a stockpile of stored LRE. The experiments were made in a test station and the NEFF620 real-time digital system was adopted. The typical experimental results of the combustion chamber pressure, the propellant flow rate, the thrust of the LRE, and the outlet pressure of pressure regulator and pressure stabilizer were obtained at starting, stable and stopping sections. The experimental results indicate that the data of the three experiments are consistent and the LRE possesses good starting characteristic after being stored for certain years, at stopping section the parameters changes are similar to each other, the parameters switch to final working state quickly after receiving a preliminary signal of stopping, there exists an obvious flatbase effect, the LRE still has a good carrying precision, and the regulating performances of both the pressure regulator and the pressure stabilizer are fine enough to meet the demands of normal working state of LRE. The conclusions can be used as a reliable basis for the performance examination and the design of advanced LRE, and are important for the theoretical investigation and numerical computation.

关 键 词： 热试车 实验研究 液体火箭发动机 数据采集 推力 压力 推进剂 启动特性

领　　域： [航空宇航科学与技术] [航空宇航科学技术]