针对大长细比飞行器外形超声速大迎角条件下前置小翼展开过程引起的非定常问题，应用结构动网格技术和基于脱体涡模拟（DES）的非定常数值模拟技术进行了研究，获得了详细的小翼展开过程流场结构非定常变化特性，并分析了小翼展开引起的法向力、纵向压心系数等气动特性随展开角度的变化规律。研究结果表明：超声速大迎角条件下前置小翼展开过程对小翼附近区域以及尾舵区域产生了强烈的干扰影响。小翼完全展开后，压心前移4.1%，降低了飞行器静稳定性，法向力系数增加15.6%，提高了气动过载，对飞行器机动性能均产生有利影响。
To research the unsteady performance of a supersonic vehicle during spreading of the front wings at high angle of attack, an unsteady numerical method based on the moving structure grid technique and Detached Eddy Simulation (DES) has been developed. The process of spreading of the front wings for a supersonic vehicle with large slenderness ratio has been investigated. Detailed unsteady progress of the flow field structure during spreading of the front wings is obtained. Variation in the aerodynamic characteristics such as the normal force coefficient and the center of pressure with spread angles of the front wing is analyzed. The results show that there is obviously unsteady effect and intense interference on the regions around the front wings and rear fins at high angle of attack during spreading of the front wings. After the spreading of the front wings, the center of pressure of the vehicle is moved forward by about 4.1%, and the static stability of the vehicle is reduced. Moreover, the normal force coefficient is increased by about 15.6%, and the aerodynamic overload is improved. These variations are good for enhancing the maneuverability of the vehicle.
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