载人飞船返回舱的压力分布  

THE PRESSURE DISTRIBUTIONS OF CAPSULE TYPE RE-ENTRY VEHICLE

作　　者：赵梦熊[1] 

机构地区：[1]中国航天工业总公司第七一○研究所

出　　处：《气动实验与测量控制》1995年第3期1-8,共8页

摘　　要：载人飞船小升阻比返回舱的再入轨道主要取决于配平升阻比、弹道系数和再入点的轨道倾角。风洞试验测出的球冠压力分布与理论计算值和飞行试验值均较符合，可以用于实际飞行。气流分离和真实气体效应对倒锥锥面的压力影响较大。拐角半径增大，使拐角和球冠区的压力降低，而使锥面压力增大。雷诺数和边界层状态对底压系数的影响较大。This paper presents the re-entry trajectorics and pressure distributions of re-entry module of manned spacecraft. The re-entry trajectories of descent module are determined mainly by trim lift-to-dragratio, ballistic coefficient, and flight path angle of atmospheric entry.The wind tunnel measured pressures on the spherital nose segment are in good agreement with flight measurement, and theoretical predictions. The pressures of conical section are greatly influenced by flow seperation, andreal gas effect .The pressures of spherical segment increases, and the pressures of conical section decreases with increasing radius of cornered toroid.The base pressure coefficients are influenced by Reynolds number, and the boundary layer conditions.

关 键 词：载人飞船 返回舱 再入轨道 压力分布 风洞试验 

分 类 号：V414.1[航空宇航科学与技术—航空宇航推进理论与工程] V412.41