跨大气层飞行器爬升段纵向飞行控制律和制导律设计

由于火箭发动机的巨大推力，跨大气层飞行器在爬升段加速很快，重量、重心、惯量、飞行速度以及飞行高度等参数变化剧烈，无法简单地用固定控制增益参数的形式来保证整个飞行包线内的飞行品质要求。根据飞行器的爬升特点和控制难点，在爬升段的飞行包线内选择典型设计点，分别进行纵向内外回路控制律的详细设计。采用控制增益参数随动压变化进行调参的方法，对爬升段飞行轨迹进行了数字仿真，结果表明设计的控制增益参数及控制律，满足了跨大气层飞行器爬升段的预定目标要求。

Longitudinal Flight Control and Guidance Law Design for Trans-aerosphere Vehicle During Climbing Phase

During the accelerated climbing phase, the parameters, such as weight, center of gravity, inertia, flight velocity and altitude are very quickly changed for trans-aerosphere vehicle (TAV). It is difficult to ensure flying qualities by simply using constant controlling gains in the whole flight envelope. According to these considerations, several typical design points of the flight envelope are selected to design longitudinal inner and outer control law. The method for controlling gains scheduled by the pressure is used to digitally simulate the flight path. Simulation results show that the designing gain parameters are reasonable and meet the TAV scheduled climbing goal.