为满足战术导弹方案设计初期对计算精度和效率的需求,建立了一种具有中等计算精度的亚声速导弹气动力快速评估方法。采用涡格法计算导弹升力、压力中心、尾舵效率以及动导数,基于部件叠加原理来评估阻力。对某战术导弹计算分析后,结果表明:当马赫数在0.3~0.6,攻角在0~8°范围时,该方法各气动参数的最大计算误差在15%以内,且单个状态点的计算时间不超过20s,在概念设计阶段具有较好的计算精度和较高的计算效率。

Accurate and economical estimates of the aerodynamic characteristics are vital for missile preliminary design. A rapid mediumfidelity method is presented to predict the aerodynamics of subsonic missiles. The vortex lattice method is used to calculate the lift, center of pressure, tail fin efficiency as well as dynamic derivatives. The missile drag is component based and accounts for the wing drag and fuselage drag. A tactical missile is studied as a case. The analysis indicates the maximum error of aerodynamic parameters is within 15% over the flight Mach number range of 0. 3 to 0.6, angle of attack from 0 to 8deg and the time penalty of a single operating condition is less than 20 seconds. The results confirm both accuracy and efficiency of the proposed numerical method.