导弹大攻角高机动飞行特性分析与仿真

Analysis and simulation of missile's high maneuver flying at high angles of attack

以新一代无翼式气动布局导弹为背景,在大攻角气动特性理论基础上,分析了在导弹主动段、攻角在180°范围内变化的导弹飞行特性,得出了90°内大攻角最大转弯能力和180°攻角附近最大降速效果的结论。进行了俯仰平面S型轨迹机动飞行仿真,仿真结果说明了大攻角飞行的高机动特性。

Based on the aerodynamic characteristics of space shuttle booster-like missile bodies at an-gle of attack from 0°to 180° , the flying characteristics of high maneuver at 90° angle of attack and velocity consuming at 180°angle of attack are analyzed. Then S-style high maneuver trajectory with high angles of attack is simulated by given control commands of angle of pitch.