关键词: 临近空间, 高超声速, 武器投放, 飞行器, 动网格

Abstract:

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 separation. 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 magnitude 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.

Key words: near space, hypersonic, weapon separation, vehicles, dynamic grid