短距起飞垂直着陆推力矢量无人飞行器减速过渡控制律设计

陈坤; 史志伟; 龚正

doi:10.13224/j.cnki.jasp.2015.12.025

短距起飞垂直着陆推力矢量无人飞行器减速过渡控制律设计

doi: 10.13224/j.cnki.jasp.2015.12.025

南京航空航天大学航空宇航学院, 南京 210016

基金项目:

江苏高校优势学科建设工程资助项目

江苏省普通高校研究生科研创新计划(KYLX_0217)

详细信息

作者简介:
陈坤(1986-),男,江苏徐州人,博士生,研究方向为飞行力学与飞行控制.

中图分类号: V212.5
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- 文章访问数: 1135
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- 被引次数: 0
出版历程
- 收稿日期: 2014-12-24
- 刊出日期: 2015-12-28

Deceleration transition control law design for short take-off vertical landing unmanned aerial vehicle with thrust vector

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 为实现短距起飞垂直着陆(STOVL)无人飞行器在推力矢量控制下的减速过渡,研究减速过渡阶段的控制律综合设计方法.首先通过分析STOVL无人飞行器减速过渡性能,对减速过渡推力矢量控制方案进行了评估;然后采用隐式动态逆方法设计导引律,为STOVL无人飞行器按预设任务减速过渡提供可达的控制指令;最后采用改进的特征结构配置方法进行内环控制律设计,跟踪导引指令并保持姿态稳定,伴随动压降低加入姿态喷管控制,辅助气动舵面稳定姿态.由全量六自由度飞行仿真结果表明:当减速过渡速度低于最小平飞速度以后,STOVL无人飞行器依然保持良好的航迹跟踪和姿态稳定.该方法完全采用直接配置法,有利于随控布局总体方案的快速评估.
- 减速过渡 /
- 短距起飞垂直着陆 /
- 推力矢量 /
- 动态逆 /
- 特征结构配置
Abstract: In order to achieve the deceleration transition of short take-off vertical landing (STOVL) unmanned aerial vehicle (UAV) with thrust vector, a comprehensive control law design method for deceleration transition was studied.First, the deceleration transition thrust vectoring control schemes were evaluated based on the analysis of STOVL UAV deceleration transition performance.Then implicit dynamic inversion method was used to design guidance laws which provide guidance instructions for STOVL UAV deceleration transition mission.Finally, an improved eigen-structure assignment method was applied for the inner loop control laws design, enabling to track guidance instructions and maintain stable attitudes; the attitude nozzles were joined for the attitude control with the drop of dynamic pressure.Results from six degree of freedom (DOF) flight simulation platform show that, when the deceleration transition speed is lower than the minimum level flight speed, STOVL UAV still keeps favorable trajectory tracking and stable attitude.Deceleration transition integrated control laws fully adopt direct collocation methods, making it conducive to rapid assessment for control configuration of vehicle program.
- deceleration transition /
- short take-off vertical landing /
- thrust vector /
- dynamic inversion /
- eigen-structure assignment

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