高马赫数临近空间无人机气动布局设计分析

Aerodynamic configuration design and analysis of near-space high supersonic unmanned aerial vehicle

以高马赫数临近空间无人机概念方案设计为背景,研究高马赫数无人机气动布局设计问题。为提高气动布局设计的效率,开发了气动外形设计和分析的工具,包括参数化几何建模程序、网格自动生成程序、自动化流场计算程序和结果分析程序。针对高马赫数无人机总体设计要求,提出一种翼身融合的双后掠气动布局方案,翼型为菱形,尾翼构型为V型。为了满足进气道进口流量捕获面积的要求,机体前缘设计成拱形前缘。应用数值分析方法分析展弦比和上反角对升阻比的影响,优选出合适的展弦比和下反角,形成了最终的气动布局方案。流场特性分析结果证实了最终的气动布局方案的合理性。

Aerodynamic configurations in the conceptual design of a near-space HSUAV（ high supersonic unmanned aerial vehicle） were investigated. To accelerate the aerodynamic configuration design process,a set of tools for the aerodynamic configuration design and analysis,including the parametric geometry modeling code,the grid generation script,the flow field analysis software and the aerodynamic result analysis code,were developed. Following the request for proposal of the HSUAV,an aerodynamic configuration for the HSUAV,in which the wing was integrated into fuselage,was proposed. The wing used a double-wedge airfoil,and the empennage was in V tail. In order to meet the requirement of the air mass flow captured by the inlet,the straight leading edge of the HSUAV was modified into the arched leading edge. Numerical simulation method was employed to evaluate the aerodynamic characteristics of the HSUAV configurations with different wing aspect ratios and dihedrals. Based on the evaluations,the most suitable wing aspect ratio and dihedral were selected,and the final aerodynamic configuration for the HSUAV was obtained. The viability of the final aerodynamic configuration of the HSUAV was verified by the detailed flow field analysis.