摘要
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 research of air combat tactics, the control of aircraft load vector（ normal load, roll angle and engine state or aircraft velocity）has been often used as the input control to resolvethe expected flight dynamic parameters. Based on the flight path characteristics and pilot＇ s control habit, with the consider-ation of the limits of aircraft performance, the control law for circling, zooming, diving, accelerating/decelerating, looping, route flight was designed. Simulation results indicate that the design control law can meet the requirements for aircraft conventional maneuvers, which is practical for air combat tactics simulation.
出处
《飞行力学》
CSCD
北大核心
2013年第3期213-216,共4页
Flight Dynamics
基金
陕西省电子信息系统综合集成重点实验室资助(2011ZD004)
关键词
机动
动力学
飞行仿真
过载控制
maneuver
dynamics
flight simulation
load control
