磁悬浮助推发射气动力分析及风洞试验  

Aerodynamic analysis and wind tunnel testing on maglev launch assist

作　　者：陈晓东[1] 杨文将[1] 刘宇[1] 段毅[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《航空动力学报》2007年第9期1560-1564,共5页Journal of Aerospace Power

基　　金：国家863基金

摘　　要：通过分析磁悬浮助推发射装置的空气动力特征,提出了其气动外形设计的合理原则.分析了磁悬浮橇体和支撑分离机构的气动外形方案,并确定了优化的气动外形设计参数值.考虑地面效应模拟的同时,在FD-06风洞中进行了缩比模型试验.结果表明,升阻力系数随着马赫数或运载器迎角的增大而增大,装置有上仰的趋势,迎角为0°时,阻力系数较小,各系数的变化也较小.The aerodynamic characteristics of a maglev （or magnetic levitation） launch assist vehicle were analyzed and rational design principles for its aerodynamic shape were proposed. The aerodynamic shape configuration for the maglev sled as well as for the support and separation structure was analyzed and the optimal values of design parameters were obtained. A wind tunnel testing for a scale model was made in the FD-06 wind tunnel, in which simulation ground effect was considered. The results show that the lift and drag coefficient increases along with the increase of Mach number or the attack angle of the space vehicles. The launch assist vehicle has a tendency to face upward. When the attack angle is zero, the drag coefficient is relatively small and the variation of each coefficient is relatively small too.

关 键 词：航空、航天推进系统 磁悬浮 助推发射 风洞试验 空气动力 

分 类 号：V211.24[航空宇航科学与技术—航空宇航推进理论与工程]