超声速炮射飞行器控制面故障数值诊断方法  

Numerical Diagnosis Method for Control Surface Faults of Supersonic Gun-Fired Aircraft

作　　者：余奕甫 王兵[1] 王强[2] 金鑫[2] YU Yifu;WANG Bing;WANG Qiang;JIN Xin(Tsinghua University, Beijing 100084, China;China Academy of Aerospace Aerodynamics, Beijing 100074, China)

机构地区：[1]清华大学航天航空学院,北京100084 [2]中国航天空气动力技术研究院,北京100074

出　　处：《兵器装备工程学报》2020年第9期25-28,41,共5页Journal of Ordnance Equipment Engineering

基　　金：国家自然科学基金项目(11572303)。

摘　　要：针对鸭式布局炮射超声速飞行器飞行试验的发射、巡航过程中出现的翼、舵损坏严重的问题,对全模型飞行试验状态下的空间流场进行数值模拟并对损坏部件局部流场结构进行分析,数值模拟的结果表明:当来流Mach数Ma=5时,在三种海拔高度下,小攻角状态弹体头部产生的强激波是鸭翼损坏的直接因素,助推器前缘位置激波是尾舵损坏的直接因素,控制面结构前后巨大的静压差导致了舵机结构的破坏。通过对试验攻角工况下弹体局部流场流动参数的分析,得出翼、舵损坏的气动影响因素,为气动布局的改进提出了合理的建议。For the serious damage of wing and rudder of canard-shaped gun-launched supersonic tactical aircraft during the launch and cruise process off light test,the numerical simulation of space flow field under full aircraft model from flight test was carried out and the local flow field structure of damaged components was analyzed.The results of numerical simulation show that when the Mach number Ma=5 of the incoming flow at 3 altitudes,the strong shock wave generated at the nose of the projectile body at low angle of attack is the direct cause of the damage of the canard wing,and the shock wave at the leading edge of the booster is the direct cause of the damage of the stern rudder,and the huge static pressure difference between the front and back of the control surface structure leads to the damage of the rudder structure.Through the analysis of the flow parameters of the local flow field of the projectile body at the test angle of attack,the aerodynamic factors affecting the damage of the wing and rudder were obtained,and reasonable suggestions for the improvement of the aerodynamic layout were put forward.

关 键 词：超声速炮射飞行器 翼面故障 舵面故障 流动结构 数值诊断 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]