某型无人机助推火箭推力线偏差优化设计及安全影响分析  

Optimal Design and Safety Impact Analysis of Thrust Line Deviation of Rocket-assisted UAV

作　　者：袁小磊 张栋 马少博 邵振宇 朱寓卿 YUAN Xiaolei;ZHANG Dong;MA Shaobo;SHAO Zhenyu;ZHU Yuqing(Aerospace Times Feihong Technology Company Limited,Beijing 100094,China)

机构地区：[1]航天时代飞鸿技术有限公司,北京100094

出　　处：《机械制造与自动化》2025年第2期258-261,共4页Machine Building & Automation

摘　　要：火箭助推发射是一种应用广泛的无人机起飞方式,推力线偏差是火箭助推无人机安全平稳发射的关键。针对某型中程高速固定翼无人机,制定推力线偏差测量方法,结合动力学仿真模型对推力线偏差进行安全影响分析,得出推力线偏差最优设计范围。飞行试验结果表明:该设计合理可行,可作为无人机推力线调整定量标准,能够保证无人机安全可靠发射。Rocket-assisted launch is a widely used method for UAV take-off,and thrust line deviation is the key to the safe and stable launch of rocket-assisted UAV.This paper formulates a measurement method for thrust line deviation for a certain medium-range high-speed fixed-wing UAV,and analyzes the safety impact of thrust line deviation combined with a dynamic simulation model,obtaining the optimal design range of thrust line deviation.The flight test results show that the design is reasonable and feasible,and can be of quantitative standard for UAV thrust line adjustment ensuring safe and reliable UAV launch.

关 键 词：火箭助推 固定翼无人机 推力线 安全影响 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]