摘要
研究了采用自适应控制系统的无垂尾构型推力矢量飞机的飞行控制性能。论述了在有参数未知的情况,使用状态变量反馈可线性化的非线性系统的输出轨迹的控制问题,推导出了自适应控制律的设计方法。最后,针对算例飞机给出了仿真计算的结果,证实了在无垂尾构型推力矢量飞机上应用自适应控制系统的可行性。
In this paper, the design of an adaptive control system of the vertical tailless aircraft with thrust vectoring control was presented, and the problem of output trajectory control of the typical input-output feedback linearizable nonlinear dynamic system by state variable's feedback is considered. An adaptive control system is designed for a specific aircraft by the design method of the adaptive control system introduced in the paper. Some results are given, and the feasibility and correctness of the design of the adaptive control system then is confirmed.
出处
《飞行力学》
CSCD
2004年第4期9-12,共4页
Flight Dynamics
基金
航空基金资助项目(00A51049)
关键词
推力矢量
自适应控制
无垂尾构型
thrusting vector
adaptive control
vertical tailless aircraft
