迎角对导弹初始弹射弹道的影响

针对导弹发射的机弹分离过程存在较大不稳定性问题，通过求解流体动力学方程组和刚体六自由度运动方程，仿真分析了迎角对空空导弹初始弹射弹道的影响。参照美国阿诺德工程发展中心开展的一项使用标准机翼/挂架/带舵外挂物模型的捕获轨迹法试验，建立了相似的几何仿真模型并进行了数值计算。通过数值计算结果与文献［29］中风洞试验结果进行对比分析，验证了数值计算方法的可行性；采用该方法计算和分析了四代战机在不同迎角下内埋弹射空空导弹的初始弹道。结果表明：在超声速条件下，迎角变化对导弹初始弹射阶段的六自由度运动有明显的影响；随着迎角的增大，导弹俯仰运动更剧烈、横滚角度更大、偏航角度更小，机弹分离的速度明显下降、分离的安全性逐渐降低。

Influence of Angle of Attack on Initial Ejection Trajectory of Missile

For the instability of separation process of missile, the influence of angle of attack on the initial ejection trajectory of air-to-air missile is analyzed by solving fluid dynamics equations and 6DOF equations of rigid body. Referring to American AEDC's captive trajectory system (CTS) testing, in which uses a generic wing/pylon/finned store model, a similar geometric model is established and numerical calculation is carried out. The feasibility of the numerical calculation method is verified by comparing the numerical results and the CTS results in Ref.［29］. The method is used to calculate and analyze the initial trajectory of an air-to-air missile launched from a fourth-generation fighter under different angles of attack. The following laws are revealed by the analysis: under supersonic condition, 6DOF motion of missile is apparently influenced by the angle of attack at the initial ejection stage. With the increase in the angle of attack, the pitch motion of missile becomes more intense, the roll angle becomes larger, and the yaw angle becomes smaller. The velocity of missile-separation from aiacraft decreases obviously, and the safety of missile-separation from aiacraft decreases gradually.