空气舵/推力矢量复合控制技术研究及其仿真

Study on Complex Control Method of Air Helm/ Thrust Vector and Attack Angle Compensation

为解决高升阻比的面对称升力体气动外形造成风剪区干扰力矩大,控制力矩不足导致喷管摆角需求超过最大允许值的问题,进行了姿态控制技术研究;采用了空气舵\推力矢量复合控制以及计攻角补偿的方法,提高控制能力的同时,又有效减小了风剪区的攻角,使喷管摆角需求降低到允许值以内;研究结果保证了导弹可以通过风剪区,并对相应的控制方法建立六自由度模型,在matlab的仿真环境下进行了仿真验证,有较好的工程实际应用价值。

In this paper,our objet model is based on a new generation aircraft.Aim at the disadvantage of large disturbing moment in V wind region and nozzle angle beyond its limit,a complex control system was designed,which used the compound control of air helm and thrust vector.An estimating method of attack angle was designed to compensate pitching angle.All the methods effectively reduced the impact of wind and ensured the aircraft cross V wind region successfully.A mathematical model was built and simulated in matlab and simulink.The results show that the control methods are correct,and all the methods are valuable for engineering application.