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细长体飞行器在大迎角绕流时,一般存在非对称分离的问题.对带三组翼面的细长体飞行器模型,通过在自由来流中加入随机脉动,开展了大攻角横侧向气动力不确定性的数值模拟研究.基于流场结构的物理分析表明,横侧向气动力的不确定性来源于弹身非对称分离涡对扰动的高度敏感性.基于这一认识,进一步分析了不同布局飞行器气动不确定性差异的原因及其随迎角的变化规律.最后,根据地面模拟与实际飞行条件的差别,模拟了快速拉起动作和突发短暂的大气扰动等非定常现象对飞行器气动不确定性的影响.结果表明,该飞行器在实际飞行时,气动不确定性比静态结果小很多,应该能够实现可控的机动飞行.
Slender body aircraft generally have the problem of asymmetric separation when passing around a high angle of attack. For a slender body aircraft model with three wing groups, by adding random pulsation in free flow, Numerical simulation of aerodynamic uncertainties. Physical analysis based on the flow field shows that the lateral aerodynamic uncertainty comes from the high sensitivity of the asymmetric separation vortex to the disturbance. Based on this understanding, The reasons for the difference of aerodynamic uncertainties of aircraft with different layouts and their variation with the angle of attack are analyzed.Finally, based on the difference between the ground simulation and the actual flight conditions, the unsteady phenomena such as rapid pull-up action and sudden brief atmospheric disturbance are simulated On the aerodynamic uncertainty of the aircraft.The results show that the aerodynamic uncertainty of the aircraft during flight is much smaller than that of the static one and the controllable maneuver flight should be achieved.