临近空间高超声速飞行器武器投放影响因素  

Influencing factors of weapon separation of hypersonic vehicles in near space

作　　者：崔玉红[1] 徐艺哲 吕凡熹 赵飞[2] 张宇佳 孙佳濛 左光 CUI Yuhong;XU Yizhe;LYU Fanxi;ZHAO Fei;ZHANG Yujia;SUN Jiameng;ZUO Guang(School of Mechanical Engineering,Tianjin University,Tianjin 300072,China;Qian Xuesen Laboratory of Space Technology,China Academy of Space Technology,Beijing 100094,China;Land Space Technology Corporation Ltd.,Beijing 100176,China)

机构地区：[1]天津大学机械工程学院,天津300072 [2]中国空间技术研究院钱学森空间技术实验室,北京100094 [3]蓝箭航天空间科技股份有限公司,北京100176

出　　处：《航空学报》2023年第24期52-68,共17页Acta Aeronautica et Astronautica Sinica

基　　金：CAST创新基金(CAST-2020-02-04)。

摘　　要：为了深入分析临近空间高超声速飞行器武器投放的可行性,解决地面试验难以模拟复杂工况的难题,对临近空间高超声速飞行器的飞行高度、载机攻角和导弹初始安装角、弹射力大小和弹射力作用时间5个影响因素进行研究。数值模拟利用动网格流体-动力学双向耦合方法,求解了不同工况下导弹投放的姿态变化。结果表明:负攻角有利于快速和安全地完成机弹分离任务,当载机攻角由4°调整为-4°时,X轴方向角位移由5.49°减小到-6.98°,导弹抬头趋势完全消失。随着飞行高度的增加,导弹抬头趋势逐渐消失,飞行高度35 km时导弹位移和角位移都有利于机弹分离。初始安装角对导弹位移和角位移的影响显著,初始安装角从5°调整为-3°时,导弹Z轴负向位移提升了36.23%,Z轴负向角位移提升了184.24%,负初始安装角各个方向位移和角位移都具有显著的优势。弹射力大小和作用时间直接影响导弹投放姿态,弹射力大小20 kN、作用时间0.05 s是最佳的弹射力组合。研究可为临近空间高超声速飞行器武器投放的可行方案及科学预测提供参考。To thoroughly analyze the feasibility of hypersonic vehicle weapon separation in near space and address the challenge of simulating complex conditions in ground tests,we investigate five influencing factors:Flight altitude,aircraft angle of attack,initial installation angle of missile,ejection force magnitude,and ejection force action time.The attitude change of the missile launch under different operating conditions is solved by numerical simulation with the dynamic grid fluid-dynamics two-way coupling method.The results show that the negative angle of attack is conducive to the fast and safe completion of aircraft-missile separation tasks.When the aircraft angle of attack is adjusted from 4°to−4°,the angular displacement in the X-axis direction decreases from 5.49°to−6.98°,and the missile head-up trend disappears completely.As the altitude increases,the missile head-up trend gradually disappears,and both the missile displacement and angular displacement at the flight altitude of 35 km are favorable to aircraft-missile separa⁃tion.The effect of the initial installation angle on the missile displacement and angular displacement is significant.When the initial installation angle is adjusted from 5°to−3°,the missile negative displacement in the Z-axis increases by 36.23%,the negative angular displacement in the Z-axis increases by 184.24%,and the negative initial installation angle has significant advantages in all directions of displacement and angular displacement.Ejection force magnitude and ejection force action time directly affect missile launch attitudes.The optimal combination is the ejection force mag⁃nitude of 20 kN and the ejection force action time of 0.05 s.This research can provide a reference for feasible options and scientific prediction for weapon separation of hypersonic vehicle in near space.

关 键 词：临近空间 高超声速 武器投放 飞行器 动网格 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]