摘要
提出楔形升力体高超声速飞行器两锥构型的参数化建模方法。所设计外形控制参数物理意义明确,能精细地刻画飞行器外形,并在设计空间产生丰富的构型拓扑。通过参数设计和改变控制面型线,分别获得了翼曲面上反平底外形、翼曲面上反无平底外形、翼平面上反平底外形及无上反平底外形4类典型拓扑。对4种构型进行分析,结果表明:楔形升力体质心较为靠后,"平底+上反"可提高容积和容积率,翼平面上反平底构型具有较优秀的综合气动特性。
A parametric modeling method is proposed for a double-cone wedge-lifting-body hypersonic vehicle. The designed shape control parameters have clear physical meaning which can describe vehicle＇s shape elaborately and generate large numbers of configuration topologies in shape design space. By designing parameters and changing control-surface profile, four typical topologies are generated： wing curved surface shape with dihedral and flat-bottom, wing curved surface shape with dihedral but no flat-bottom, wing plane surface shape with dihedral and flat-bottom, and wing plane surface shape with flat-bottom but no dihedral. CATIA and CFD analysis results show the centroid of wedge-lifting-body is relatively near the back-end. The combination of flat bottom and dihedral can improve the volume and the volume fraction of the vehicle. Thus the wing plane surface shape with dihedral and flat-bottom has the more outstanding comprehensive aerodynamic characteristic.
出处
《导弹与航天运载技术》
北大核心
2015年第6期6-12,共7页
Missiles and Space Vehicles
基金
国家自然科学基金(11272062)
关键词
楔形升力体
高超声速
参数化建模
容积率
气动特性
Wedge-lifting-body
Hypersonic
Parametric modeling
Volumn fraction
Aerodynamic characteristics
