三维内转进气高超声速导弹气动布局研究

Research on Aerodynamic Layout of Three-Dimensional Inward Rotating Inlet Hypersonic Missile

基于三维内转进气道开展高超声速导弹气动布局研究,重点针对曲锥弹身开展了颌下进气与两侧进气两种气动布局研究。数值仿真结果表明,颌下进气布局在特定的攻角下利用弹身前体预压缩效果,具有较高的进气道性能。两侧进气布局无法有效利用前体的预压缩效果,较难构造高性能的内部流场,但能够利用进气道产生升力,使全弹具有较好的气动特性。此外,两侧进气布局具有更小的攻角敏感性,在攻角变化过程中,整体性能变化较小。因此,颌下进气布局适用于单点巡航的导弹设计,两侧进气布局适用于攻角变化范围要求高的导弹设计。

Based on the three-dimensional inward rotating inlet,the aerodynamic layout of hypersonic missile is studied,focusing on the submaxillary inlet and the inlet on both sides.The numerical simulation results show that the submaxillary inlet layout has high inlet performance by using the pre-compression effect of the missile’s precursor at a specific angle of attack.The inlet layout on both sides can not effectively use the pre-compression effect of the precursor,and it is difficult to construct a high-performance internal flow field,but it can use the inlet to generate lift,so that the whole missile has better aerodynamic characteristics.In addition,the inlet layout on both sides has less angle of attack sensitivity,and the overall performance changes less during the change of angle of attack.Therefore,the submaxillary inlet layout is suitable for the design of single point cruise missile,and the inlet layout on both sides is suitable for the design of missile with high requirements for angle of attack variation range.