液氧煤油发动机高空条件下后效冲量研究  

Research on Cutoff Impulse of High Altitude for LOX/Kerosene Staged Combustion Cycle Engine

作　　者：李程[1] 周丽兵 吕顺进 张锋[1] 马楠 Li Cheng;Zhou Li-bing;Lyu Shun-jin;Zhang Feng;Ma Nan(Xi’an Aerospace Propulsion Institute,Xi’an,710100;Academy of Aerospace Propulsion Technology,Xi’an,710100)

机构地区：[1]西安航天动力研究所,西安710100 [2]航天推进技术研究院,西安710100

出　　处：《导弹与航天运载技术》2019年第2期39-43,共5页Missiles and Space Vehicles

摘　　要：新型运载火箭发动机关机后效冲量影响火箭飞行弹道精度,对火箭飞行的弹道设计和飞行时序设计意义重大。通过对液氧煤油发动机高空条件下后效冲量的评估方法的总结,评估了180kN液氧煤油发动机高空条件下后效冲量时间分布特性:关机后2.5s内,无量纲后效冲量为1±0.15;2.5s后,不考虑推进剂泄漏时,无量纲后效冲量最大值为0.06;泄漏推进剂产生的无量纲后效冲量为1.55×10^(-4)·t。研究结果表明:采用该方法评估的后效冲量与火箭飞行实测数据评估结果吻合,验证了液氧煤油发动机高空条件下后效冲量评估方法的正确性。LOX/Kerosene rocket engine is mainly applied in the new generation launch vehicle,the cutoff impulse of high altitude for rocket engine is an important factor which influences the flight trajectory precision.The result of cutoff impulse for LOX/kerosene engine is of signality for the liquid rocket trajectory design and stage separation sequence.The evaluation method of cutoff impulse under high altitude conditions for the 180kN thrust LOX/Kerosene rocket engine is summarized.The dimensionless cutoff impulse is 1±0.15 within 2.5 seconds,and the maximum dimensionless cutoff impulse is 0.06 after 2.5 seconds when the leakage propellant is not considered,the dimensionless cutoff impulse produced by leaking propellant is 1.55×10^-4·t.The result is agreed well with the flight result,demonstrating the correction of the evaluation method of the cutoff impulse for the LOX/Kerosene rocket engine.

关 键 词：液氧煤油发动机 后效冲量 评估方法 分布特性 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]