摘要
MF-1是我国的首次高超声速空气动力学基础问题研究模型飞行试验。本文研究建立了MF-1试验飞行器弹道设计与拉偏仿真数学模型,开展了MF-1弹道设计和拉偏仿真计算。对结果分析表明,对于MF-1这类无控飞行器,某些条件下可能在飞行过程中发生滚转共振现象,导致飞行总迎角迅速发散,气动过载显著增加,飞行弹道严重偏离设计弹道,甚至可能出现解体风险。通过严格控制飞行器加工和安装偏差,有助于降低滚转共振发生概率。
MF-1 is the first modeling flight test in China aiming at fundamental hypersonic aerodynamics problems.In this paper,the models of trajectory design and Monte Carlo flight simulation for MF-1 are established,and the results of designed trajectory and Monte Carlo flight simulations are presented.Results analysis shows that,for MF-1-like flight vehicles,the roll resonance phenomena may happen in some circumstances.These phenomena can produce unstable total flight angle of attack and increasing aerodynamic overloads,leading to trajectory parameters deviating from designed values,and risks of structural collapse.Moreover,the roll resonance can be suppressed by strictly limiting the errors and bias during producing and manufacturing procedures.
作者
和争春
车竞
肖涵山
袁先旭
HE Zhengchun;CHE Jing;XIAO Hanshan;YUAN Xianxu(State Key Laboratory of Aerodynamics,Mianyang 621000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China)
出处
《空气动力学学报》
CSCD
北大核心
2019年第2期201-206,共6页
Acta Aerodynamica Sinica
