高空飞艇高度控制系统设计及仿真

高空飞艇在上升和下降阶段时单独的空气舵控制或副气囊充放气操纵都难以实现飞艇的快速爬升和悬停的要求。针对高空飞艇纵的控制操纵特点，提出了采用副气囊充放气和空气舵组合控制的高空飞艇高度控制方案。当时高度存在大误差时，采用副气囊和空气舵组合控制改变飞艇的姿态实现快速爬升或下降；当接近悬停高度时，主要采用副气囊充放气进行高度调整，从而实现高度的大范围控制。首先完成了采用组合控制的高空飞艇动力学建模；然后，基于最优控制对高空飞艇纵向高度控制系统进行了设计；最后给出了高空飞艇高度控制系统的仿真验证。结果表明所提出的高空飞艇组合控制方案是可行的。

High Altitude Airship Altitude Control System Design and Simulation

The high altitude airship can not have desired performance to control the altitude rapidly and accurately when the elevator and ancillary air bursa charge or deflation are used only, because the elevator has few efficiency when the velocity is low, and auxiliary ballonet charge or deflation control is very slow. It is present a method to design altitude control system for a high altitude airship using auxiliary ballonet charge or deflation and elevator combination control. This combination control scheme is that the ancillary air bursa and elevator are also used to control the airship attitude to get large raise velocity and the ancillary air bursa control is used to adjust the airship altitude for suspension. In this paper, a high altitude airship model with compound control of elevator and ancillary air bursa charging and deflation is given firstly. Then the optimum control is depicted to design the altitude control system for a high altitude airship. Finally, it has been proved by simulation that the attitude control system has desirable performance and the compound control scheme is feasible.