折叠式串列翼巡飞弹设计及验证方法研究

Research on the design and verification method of folding tandem wing patrol missile

针对小型巡飞弹在开发和验证过程中难以采用风洞进行气动参数测试的问题,在对某型9 kg级串列翼巡飞弹进行总体设计的基础上,提出一种气动仿真/地面跑车/飞行试验相结合的巡飞弹设计及验证方法。由飞行试验数据可知,实际巡航空速均值(31 m/s)与设计巡航空速(30 m/s)相差3.3%,实际巡航油门比例均值(0.70)与设计巡航油门量(0.66)相差6.1%,俯仰及滚转姿态误差≤3°,证明该方法合理可行,为该类型飞行器的设计及验证提供了一条思路。

Aiming at the difficult to test the aerodynamic parameters of the small cruise missile in the wind tunnel during the development and verification,based on the overall design of a 9 kg tandem-wing cruise missile,a design and verification method of cruise missile based on aerodynamic simulation,ground sports car and flight test is presented.According to the flight test data,the difference between the actual cruising speed(31 m/s)and the designed cruising speed(30 m/s)is 3.3%,and the difference between the actual cruising throttle ratio(0.70)and the designed cruising throttle volume(0.66)is 6.1%,the error of pitching and rolling attitude is less than 3°,which proves that the method is reasonable and feasible.