两级融合乘波空天飞机设计与气动特性研究  

Design of a Two-Stage Fusion Waverider Reusable Aerospace Plane and Investigation on its Aerodynamic Performance

作　　者：罗世彬 周嘉明 王逗 刘俊 LUO Shi-bin;ZHOU Jia-ming;WANG Dou;LIU Jun(School of Aeronautics and Astronautics,Central South University,Changsha Hunan 410083,China)

机构地区：[1]中南大学航空航天学院,湖南长沙410083

出　　处：《计算机仿真》2021年第10期38-42,共5页Computer Simulation

摘　　要：为了避免两级入轨空天飞机两子级之间存在的激波干扰,提高两级在高速阶段的气动性能,基于锥导乘波理论提出了一种上表面部分融合的两级融合乘波气动布局设计方法,并采用数值模拟方法研究了该布局的气动特性。计算结果表明,乘波体距离基准锥轴线距离的增加会提高两级的升阻比,上表面后缘线二次项系数的增加使两级的最大升阻比提高,但对上面级影响较小,当组合体不变,上面级的最大升阻比随着半展角的增加而减小。下面级在低速飞行时,由于上表面的凹陷,比组合体拥有更高的升力系数,这表明上面级的分离将提高飞行器的升力特性,使下面级拥有更好的着陆性能。In order to improve the aerodynamic performance of the two-stage to orbit spaceplane and avoid the shockwave interference between the two stages, a two-stage fusion aerospace plane design method was proposed. The aerodynamic characteristics of such aircraft were studied by numerical simulation. The results show that the increase of the distance between the midpoint of the upper surface trailing edge line and the reference cone axis has a great influence on the aerodynamic characteristics of the two stages. The increase of the quadratic coefficient of the trailing edge of the upper surface increases the maximum lift-drag ratio of the two stages, but has a relatively small impact on the upper stage. When the combination is specified, the lift-drag ratio of the upper stage decreases with the increase of the dihedral angle of the winglet. Furthermore, the lower stage has a higher lift coefficient than that of the combination due to the airflow compression on the upper surface at low fight velocity, which makes the lower stage has better landing performance.

关 键 词：乘波体 空天飞机 高超声速 两级入轨 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]