The invention provides a spine TSTO aerodynamic layout for interstage separation, and belongs to the technical field of aircraft design, and the aerodynamic layout is composed of a booster similar to a waverider and a wing body assembly. And a shock wave needle is placed at the head of the orbiter. And carrying out unsteady numerical simulation on TSTO interstage separation under Mach 6 by utilizing computational fluid mechanics. Pressure cloud pictures, pitch angles and displacement changes of the two models are compared. Under the interference of the shock wave needle, the flow field of the bluff body shows obvious asymmetry. The oblique shock wave of the leeward side is weaker than that of the windward side, and the area, influenced by the shock wave, of the windward side gradually moves towards a stagnation point along with the increase of the attack angle, so that the safety of the two-stage separation process is improved by changing the flow field structure. In addition, under the condition that the aerodynamic layout of the aircraft is not changed, aerodynamic interference between the two stages is reduced through the shock wave needle, and therefore resistance is reduced.
本发明提出了一种用于级间分离的尖刺TSTO气动布局,属于飞行器设计技术领域,该气动布局由类似乘波体的助推器和翼身组合体组成。在轨道器的头部放置了一个激波针。利用计算流体力学对马赫6下的TSTO级间分离进行了非定常数值模拟。比较了两种模型的压力云图、俯仰角和位移变化。在激波针的干扰下,钝体的流场表现出显著的不对称性。背风侧的斜激波弱于迎风侧,并且迎风侧受激波影响的区域随着攻角的增加而逐渐向驻点移动,从而通过改变流场结构来提高两级分离过程的安全性。此外,在不改变飞行器的气动布局的情况下,激波针减少了两级之间的空气动力学干扰,从而减少了阻力。
Sharp TSTO aerodynamic layout for interstage separation
一种用于级间分离的尖刺TSTO气动布局
2024-03-15
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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