摘要
利用弹簧近似和网格重构相结合的非结构动网格技术,耦合求解Euler方程及弹道方程,模拟飞行在46千米高空、0°攻角、马赫数6.5、壳片分离初速分别为6m/s,12m/s、壳片分离角速度分别为0°/s,50°/s,150°/s的子母弹抛壳动态过程。研究表明,抛壳初期,壳片与母弹周围形成复杂流动,在壳片内表面存在激波的生成、发展、减弱等非定常过程,导致壳片受到气动力随着分离距离增加表现为很强的非线性特征;壳片分离初始角速度对壳片姿态的影响不是线性的,尽管分离初始角速度增加到150°/s,由于转动惯量小、俯仰力矩大,壳片实际飞行姿态达不到设计要求,壳片攻角较小,气动阻力小,导致壳片伴随母弹较长时间飞行;增大分离初速是实现快速分离的有效措施。
Spring analogy and remeshing method for dynamic unstructured grids are used to solve the problem of released the cover form cargo projectile. Solving the ALE Euler equations coupled with trajectory equations dynamically stimulates the process of releasing cover form cargo projectile at mach 6.5, attack angle 0°, 46km. The cover releasing speeds are 6m/s, 12m/s, and angular velocities are 0°/s,50°/s, 150°/s. It can be concluded from simulation results that the reduces that the aerodynamic forces of cover appears strong nonlinearity with the separation distance. The relation of angular velocities and angular attitude is also nonlinear according to simulation results. The cover will accompany with the cargo for a long period even if the initial angular velocity is 150°/s because that the inertia of the cover is relative small and aerodynamic moment is large. It can also be concluded that increasing the separating speed is beneficial to insure the safety of separation
出处
《空气动力学学报》
EI
CSCD
北大核心
2006年第3期285-288,共4页
Acta Aerodynamica Sinica
关键词
非结构动网格
多体干扰
子母弹壳片分离
数值模拟
dynamic unstructured grid
multi-body disturbance
release covers form cargo projectile
numerical simulation
