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为了改善内装式运载火箭与载机分离过程载机的飞行品质,应用现代控制理论,以一组期望的闭环极点为设计目标,利用正比于状态变量的线性控制律,设计带有状态观测器的状态反馈系统。通过Bass-Gura法求解反馈增益,基于时域分析法数值模拟了带有状态反馈器飞机的飞行品质。仿真结果表明,长、短周期运动变为收敛的周期模态,飞行品质提高到1级标准,可见状态反馈器设计是一种改善箭机分离过程载机飞行品质的高效可行的方法。
In order to improve the flight quality of the carrier-equipped launch vehicle and carrier-borne aircraft, a set of desired closed-loop poles is used as a design objective by applying modern control theory. A linear control law proportional to the state variables Status feedback system. The feedback gain was solved by Bass-Gura method and the flight quality of the aircraft with state feedback was numerically simulated based on time-domain analysis. The simulation results show that the long and short periodic motions become the convergent periodic modes, and the flight quality is raised to level 1 standard. It can be seen that the state feedback design is a highly efficient and feasible method to improve the flight quality of the carrier-borne aircraft.