[1]浦黄忠,甄子洋,夏 曼,等.螺旋桨无人机双发火箭助推发射过程控制研究[J].南京理工大学学报(自然科学版),2015,39(02):155-160.
 Pu Huangzhong,Zhen Ziyang,Xia Man,et al.Launching process control for propeller UAV with double booster rocket[J].Journal of Nanjing University of Science and Technology,2015,39(02):155-160.
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螺旋桨无人机双发火箭助推发射过程控制研究
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《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
39卷
期数:
2015年02期
页码:
155-160
栏目:
出版日期:
2015-04-30

文章信息/Info

Title:
Launching process control for propeller UAV with double booster rocket
作者:
浦黄忠1甄子洋2夏 曼2郭小良1
南京航空航天大学 1.无人机研究院; 2.自动化学院,江苏 南京 210016
Author(s):
Pu Huangzhong1Zhen Ziyang2Xia Man2Guo Xiaoliang1
1.Institute of UAV; 2.College of Automation Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
关键词:
无人机 飞行控制 发射过程
Keywords:
unmanned aerial vehicles flight control launching process
分类号:
V249
摘要:
研究了螺旋桨无人机双发火箭助推发射过程的控制系统设计,分析了螺旋桨发动机离合时间和油门最大开度时间等关键参数对发射过程的影响。建立了火箭助推无人机发射过程的非线性数学模型和包括俯仰角、滚转角和航向角控制回路的飞行姿态控制系统及其仿真结构,仿真验证了飞行控制系统的有效性和螺旋桨发动机离合时间和油门最大开度时间等对无人机火箭助推发射过程的影响。仿真结果表明,飞行控制系统能够有效控制无人机发射过程的姿态,实现稳定爬升。在保证安全发射的前提下,应尽早实现螺旋桨发动机离合和油门最大开度。
Abstract:
The design of control system and simulation analysis of key parameters at the launching process of the propeller UAV with double booster rockets are studied.The nonlinear mathematical model of the UAV launching process is set up,and the flight attitude control system consisting of control loops of the pitch angle,the roll angle and the yaw angle is designed.Then the simulation system of the UAV launching process control system is established to verify the effectiveness of the flight control system,and the influence of construction time of the propeller engine and the construction time of maximum thrust are investigated.Simulation results show that the flight control system can guarantee the stable climbing through effective control of the UAV's attitudes,and the clutching of the propeller engine and the maximizing of the throttle opening should be realized as early as possible on the premise of safe launching.

参考文献/References:

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备注/Memo

备注/Memo:
收稿日期:2014-09-02 修回日期:2014-11-14
基金项目:国家自然科学基金(61304223); 教育部高等学校博士学科点专项科研基金(20123218120015); 中央高校基本科研业务费专项资金(NZ2015206)
作者简介:浦黄忠(1967-),男,博士,研究员,主要研究方向:无人机飞行控制技术,E-mail:phzh@nuaa.edu.cn; 通讯作者:甄子洋(1981-),男,博士,副教授,主要研究方向:飞行控制技术,E-mail:zhenziyang@nuaa.edu.cn。
引文格式:浦黄忠,甄子洋,夏曼,等.螺旋桨无人机双发火箭助推发射过程控制研究[J].南京理工大学学报,2015,39(2):155-160.
投稿网址:http://zrxuebao.njust.edu.cn
更新日期/Last Update: 2015-04-30