国防科技大学学报2017，Vol.39Issue(4)：62-68,7.DOI:10.11887/j.cn.201704010
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
摘要
Abstract
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.关键词
临近空间/无人机/气动布局/空气动力学Key words
near space/unmanned aerial vehicle/aerodynamic configuration/aerodynamics分类
航空航天引用本文复制引用
有连兴,余雄庆,王宇..高马赫数临近空间无人机气动布局设计分析[J].国防科技大学学报,2017,39(4):62-68,7.基金项目
中央高校基本科研业务费专项资金资助项目(NZ2016101) （NZ2016101）
国防基础科研计划资助项目(A2520110006) （A2520110006）
江苏高校优势学科建设工程资助项目 （）
