垂直/短距起降飞机的过渡段控制律设计  

Transition Control Law Design For STOVL Aircraft

作　　者：雒东超 刘超[1] 刘智汉[1] 房圣友 LUO Dong-chao;LIU Chao;LIU Zhi-han;Fang Sheng-you(China Flight Test Establishment,Xi'an Shanxi 710089,China)

机构地区：[1]中国飞行试验研究院

出　　处：《计算机仿真》2019年第8期47-50,265,共5页Computer Simulation

摘　　要：为实现在推力矢量控制下的垂直/短距起降(STOVL)飞机加减速过渡,研究过渡段的控制律综合设计方法。首先通过分析垂直/短距起降飞机的加减速过渡性能,对加减速过渡推力矢量控制方法进行了评估。然后采用改进的特征结构配置方法进行垂直/短距起降飞机加减速过渡段的控制律设计,伴随动压变化加入姿态喷管控制,辅助气动舵面稳定姿态。全量六自由度飞行仿真结果表明,当飞机加速或减速到最小平飞速度时,垂直/短距起降飞机依然具有良好的姿态稳定能力。In order to achieve the acceleration and deceleration transition of short take-off vertical landing (STOVL) aircraft, a comprehensive control law design method for transition was studied. First, the acceleration and deceleration transition vectoring control schemes was evaluated based on the analysis of STOVL acceleration and deceleration transition performance. An improved eigen-structure assignment method was applied for the acceleration and deceleration transition control law design. The attitude nozzles were joined for the attitude control with the drop of dynamic pressure to maintain stable attitudes. The results of the 6-DOF flight simulation platform show that, when the acceleration and deceleration speed is lower than the minimum flight speed, the STOVL aircraft still has good capacity of attitude maintenance.

关 键 词：垂直/短距起降 过渡段控制 推力矢量 特征结构配置 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]