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在空战战术和战法研究中,通常以飞机机动过载大小和方向(法向过载、航迹滚转角和速度/发动机状态)为输入控制量,继而解算预期动作的飞机动力学参数。根据飞机的航迹特征和飞行员操纵习惯,考虑飞机性能的限制,对飞机实现盘旋、跃升、俯冲、加减速、筋斗、按航路点飞行等常规机动的控制律进行了设计。仿真结果表明,所设计的控制律可以满足常规机动的仿真要求,具有一定的实用价值。
In the air-to-air tactics and tactics research, the aircraft maneuvering overload size and direction (normal overload, track roll angle and speed / engine state) are usually used as input control variables to solve the aircraft kinetic parameters of the expected maneuver. According to the characteristics of the flight path and pilot’s manipulation habits, considering the limitation of the aircraft’s performance, the control law of the conventional maneuver, such as hovering, jumped, subduction, acceleration and deceleration, tendon and waypoint flight, is designed. The simulation results show that the designed control law can meet the requirements of conventional maneuver simulation and has certain practical value.