论文部分内容阅读
本文主要为某超音速喷气机设计了侧向控制增稳系统的参数自适应方案,并作了数字仿真研究。目的就是应用自适应控制原理,保证飞机即使在侧向参数发生较大变化且受到外界扰动的条件下仍具有良好的飞行品质。 文中对方案的确定、增益初值的选取、控制规律的选择、自适应算法的选定以及确定方程中待辨参数的个数等问题作了分析。对飞机作定高、定速和定高、变速(减速)飞行时进行协调转弯的情况作了研究。当飞机受到随机侧风或常值侧风扰动时,也作了同上研究,并进行了对比。此外,对飞机侧向参数自适应控制增稳系统的微机实现问题作了研究,并对微机系统的设计方案进行了论证。采用Z8000型微机对滚动通道的自适应控制算法进行了试算,结果验证了其计算精度可以满足自适应侧向控制增稳系统的要求。
In this paper, a parameter adaptive scheme of lateral control stabilizing system is designed for a supersonic jet, and the digital simulation is made. The purpose is to apply the principle of adaptive control to ensure that the aircraft will have good flight quality even under the condition of large lateral parameter changes and disturbance from the outside. In this paper, the solution of the scheme, the selection of gain initial value, the choice of control law, the selection of adaptive algorithm and the determination of the number of unknown parameters in the equation are analyzed. Made a study on the situation of aircraft making a high turn, setting speed and setting high, and making coordinated turn during speed change (deceleration) flight. When the aircraft is subject to random crosswind or constant lateral wind disturbance, also made the same study, and compared. In addition, the research on the computer implementation of adaptive stabilization control system for lateral parameters of aircraft is carried out. The design scheme of the microcomputer system is also demonstrated. The Z8000 microprocessor is used to test the adaptive control algorithm of the rolling channel. The results show that the calculation accuracy of this method can meet the requirements of the adaptive lateral control augmentation system.