降低发动机羽流对飞行器干扰的研究  

Study on Reducing the Interference of Engine Plume to Aircraft

作　　者：张立坤 焦胜海 孙朝翔[1] 彭杰[1] 高达 ZHANG Likun;JIAO Shenghai;SUN Zhaoxiang;PENG Jie;GAO Da(Beijing Institute of Space Long March Vehicle,Beijing,100076;Beihang University,Beijing,100083)

机构地区：[1]北京航天长征飞行器研究所,北京100076 [2]北京航空航天大学,北京100083

出　　处：《导弹与航天运载技术（中英文）》2023年第4期128-131,共4页Missiles and Space Vehicles

摘　　要：发动机在真空环境下工作产生羽流,羽流撞击在飞行器表面产生额外的气动力,会改变飞行器在轨速度和姿态。介绍一种羽流力-推力对冲方法,通过发动机喷口角度优化,使得羽流力、推力分量大小相等、方向相反进而消除发动机工作羽流对飞行器的影响。采用跨流域耦合的NS-DSMC仿真方法优化喷口下偏角、外偏角角度;采用真空冷喷试验验证NSDSMC仿真方法的精度;采用真空罐模拟发动机工作环境,进行发动机羽流测力试验,测量喷口角度优化后平板上的合力,验证羽流力-推力对冲方法的可行性。The engine works in vacuum and produces an generates plume.The impact creates additional aerodynamic forces on the aircraft surface,which can change the on orbit speed and attitude of the aircraft.A method of plume force-thrust hedging is infroduced.The optimization of nozzle angle makes the plume force and thrust components equal in size and opposite in direction,and then the influence of engine operating plume is eliminated.The simulation method of coupling multiple physical fields NS-DSMC is used to optimize the angle of nozzle downward deflection and outward deflection.The accuracy of simulation method is verified by vacuum cold injection test.Vacuum tank is used to simulae engine working environment to test engine plume force,measure the axial resultant force after nozzle angle optimizing,and verify the feasibility of plume force-thrust hedging method.

关 键 词：羽流力-推力 对冲 真空冷喷 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]