螺旋桨无人机双发火箭助推发射过程控制研究  

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] 

机构地区：[1]南京航空航天大学无人机研究院,江苏南京210016 [2]南京航空航天大学自动化学院,江苏南京210016

出　　处：《南京理工大学学报》2015年第2期155-160,共6页Journal of Nanjing University of Science and Technology

基　　金：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)

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。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.

关 键 词：无人机 飞行控制 发射过程 

分 类 号：V249[航空宇航科学与技术—飞行器设计]