摘要
为研究不同的发射条件对透镜形武器与载机分离安全性的影响,以刚体动力学方程、嵌套网格技术结合非定常计算流体力学数值计算为研究手段,在不同的来流马赫数、初始弹射速度及发射方向下,对透镜形武器内埋弹射机弹分离过程进行模拟。结果表明:随着马赫数的增大,弹舱对弹体的气动干扰增强,弹体相对载机在X方向分离加快,Z方向分离减缓,分离过程中弹体俯仰变化加剧;弹射速度增大,在Z方向上弹体可以更快地穿越弹舱流场影响区域从而更快地离开载机,有利于机弹的安全分离;前向发射的弹体,在弹射力作用结束至弹体穿越弹舱激波干扰区域的这段时间内受弹舱流场干扰显著,出舱后存在抬头现象。后向发射的弹体受弹舱流场影响较小,能更快地与载机分离。但在无控发射条件下,出舱后弹体迅速朝前方翻转,无法实现向后发射的目的。
In order to investigate the effect of different launch conditions on the safety of separation between lenticular missile and aircraft,rigid body dynamics equations,overset grid technology combined with unsteady computational fluid dynamics numerical calculations were used as research methods to simulate the separation process of lenticular missile and the aircraft in internal store system under different incoming Mach numbers,initial ejection velocity and launch directions.The research results indicate that as the Mach number increases,the bay has an enhanced aerodynamic interference on the missile,the separation of the missile from the carrier in the X-axis direction accelerates,and decelerates in the Z-axis,and the pitch of the missile intensifies during the separation process.The increase in ejection speed allows the missile to pass through the influence area of the bay flow field more quickly in the Z direction,thus leaving the carrier more quickly,which is beneficial for the safe separation of the aircraft and the missile.The missile launched forward will be significantly affected by the flow field of the bay,during the period from the end of the ejection force to the time when the projectile passes through the shock wave interference area of the bay,which will lead to head up.The missile launched backward is less affected by the flow field of the bay,and can separate from the carrier aircraft more quickly.But under the condition of uncontrolled launch,the missile launched backwards will quickly flip forward as soon as it exits the bay,making it impossible to achieve the goal of launching backwards.
作者
戴程宇
姜毅
权亮
钱泓郡
DAI Chengyu;JIANG Yi;QUAN Liang;QIAN Hongjun(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)
出处
《弹箭与制导学报》
北大核心
2025年第5期716-725,共10页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
透镜形武器
机弹分离
嵌套网格
全向发射
计算流体力学
lenticular missile
store separation
overset grid
omnidirectional launch
computational fluid dynamics
