小型固定翼无人机零长发射参数安全边界研究  

Reasearch on Zero-Length Launch Parameters' Secure Border Investigation of Small Fixed Wing UAV

作　　者：陶于金[1] TAO Yujin(Institute of Unmanned Aerial Vehicle, Northwest Polytechnical University, Xi＇ an 710065, China)

机构地区：[1]西北工业大学无人机研究所,西安710065

出　　处：《海军航空工程学院学报》2017年第5期447-451,468,共6页Journal of Naval Aeronautical and Astronautical University

摘　　要：针对小型螺旋桨无人机零长发射仿真需求,建立了完善的发射仿真数学模型。助推火箭安装角关系到无人机发射安全,是无人机推力线吊挂工作中最重要的调整参数。结合某型无人机,实例仿真了助推火箭推力线纵向、侧向偏离重心等各种工况的发射过程,确定了火箭安装角偏移量安全边界,可作为实际推力线吊挂工作的依据。According to the requirement of zero-length launch simulation for small propeller unmanned aerial vehicle, a more refined dynamic model was proposed. The installation angle of rocket used for launching on the unmanned aerial ve- hicle could directly affect the launching safety, which is also the most important parameter to adjust in thrust line design. Based on an unmanned aerial vehicle, the launch process of booster rocket deviated from the center of gravity in longitudi- nal and lateral direction was simulated. The secure border of installation angle was conformed, which could be used as the benchmark in thrust line design.

关 键 词：小型无人机 仿真 零长发射 安全边界 

分 类 号：V279[航空宇航科学与技术—飞行器设计] V323.31