适用于吸气式高速飞行器的蚌式进气道堵盖气动设计及数值模拟研究（英文）

Design and numerical simulation of a clamshell-shaped inlet cover for air-breathing hypersonic vehicles

目的:吸气式高速飞行器在助推阶段需要对进气道采取保护措施,而应用传统的圆锥体载荷式整流罩存在体积大、质量重等缺陷。为避免载荷罩的空间雍余,基于激波干扰理论,本文旨在提出一种通用型可实现气动自分离的整流罩设计方法,并探讨设计的两组构型在两个弹道特殊状态点的气动力和气动热特性,以及研究构型的适用性和基本气动性能。创新点:1.通过激波干扰理论模型方程,推导出环境变量与构型基本尺寸之间的关系;2.建立气动设计模型,成功求得助推阶段和整流罩分离状态点的气动特性;3.新构型减轻了整流罩系统重量,实现了自分离,简化了机械结构系统。方法:1.通过理论推导,得到飞行器头锥长度和进气口尺寸变化对整流罩构型设计的影响;2.通过数值计算,得到异形整流罩及头锥附近流场分布受设计型面的影响以及产生的适应性气动力。结论:1.整流罩在分离状态可产生负升力,有自动打开的趋势;2.减小整流罩的设计长度有利于气动减阻和降低峰值热流;3.整流罩前缘的极限热流约为13 MW/m^2,在所选复合材料的受热范围内。

An efficient clamshell-shaped inlet cover configuration based on a shockwave interference methodology is proposed,which has the advantage of an autonomous opening using the aerodynamic force and moment.A preliminary design method for the inlet cover is introduced and used to produce cover models of two different lengths,with contributions similar to those of cowlings,rocket fairings,shrouds,or false ogives.The clamshell-shaped inlet cover features a practical design with a wide range of applications,including utilization in air-breathing hypersonic vehicles under specific constraints.In this investigation,aerodynamic numerical simulations were conducted to evaluate the extent to which the objectives and design principles are achieved for two typical ballistic separation states.The results show that both configurations can prevent an excessive accumulation of shockwaves in the nose cone area.In addition,the inlet cover generates negative lift,which results in the generation of an opening moment.The calculated heat flux at the leading edge of the clamshell-shaped inlet cover is approximately 13 MW/m^2,which is within the limit of the composite material but slightly higher than that of the stagnation point of the nose cone.