Abstract:

Numerical research was conducted on the near space hypersonic vehicle missile separation scheme with Mach number 4-10. We proposed four separation schemes including the missile built-in， the hatch opened with missile plug-in， the direct missile plug-in model， and the missile placed behind model. The density-based solver， the Shear Stress Transport （SST） k-ω turbulence model， the second order upwind flux format， as well as the unstructured dynamic grid technology are adopted to simulate the missile launch process with the Computational Fluid Dynamics （CFD） coupled Six Degrees of Freedom （6DOF） equation method. The flow field characteristics of four separation schemes， the influence of the Mach number on the missile separation attitude， the effect of the angle of attack on the missile separation attitude， and comparison of different separation schemes are studied. The results show that both the hatch opened with missile plug-in model and the direct missile plug-in model can be launched with a reasonable attitude in the range of Mach number 4-10， and the missile built-in model cannot be launched normally at high Mach numbers of 8 and 10， while at none of the Mach numbers can the missile placed behind model be launched normally. The initial attack angle of the aircraft of 3° will effectively improve the missile separation process. The direct missile plug-in model has the highest success rate and the least aerodynamic interference. It is therefore a relatively feasible near space hypersonic missile separation scheme. This research has an important practical value， and the attempt of the calculation method and calculation model provides technical support and reference for the subsequent numerical research on near space.

Key words: near space, hypersonic, aircraft, weapon separation, numerical simulation