航天飞机机翼外形优化的初步设计方法  

WING SHAPE OPTIMIZATION OF SPACE SHUTTLE AT THE PRELIMINARY DESIGN STAGE

作　　者：朱一锟[1] 周家胜[1] 石光煜 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系

出　　处：《北京航空航天大学学报》1997年第2期182-186,共5页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：介绍了在满足高超音速再入横向机动航程，高超音速再入飞行时的升阻比，亚音速进场飞行时的升阻比，纵向静稳定性裕度和水平着陆速度等飞行性能设计要求下，用罚函数法寻求使航天飞机机翼质量为最小的外形优化方法并给出了算例．计算结果表明，方法对初步设计阶段中航天飞机机翼外形的选择。The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re entry flight cross range,lift/drag ratio,and subsonic flight lift/drag ratio,the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc.The computed examples are given and the results are valuable for the selection of wing shape at the preliminary design stage.

关 键 词：航天飞机 机翼 最优设计 初步设计 

分 类 号：V423.8[航空宇航科学与技术—飞行器设计]