公开(公告)号：US07431242B1

公开(公告)日：2008-10-07

申请号：US11265324

申请日：2005-11-01

申请人： James L. Brown ,  Joseph A. Garcia ,  Dinesh K. Prabhu

发明人： James L. Brown ,  Joseph A. Garcia ,  Dinesh K. Prabhu

IPC分类号： B64G1/62

CPC分类号： B64G1/62 ,  B64G1/14

摘要： A convex shell structure for enhanced aerodynamic performance and/or reduced heat transfer requirements for a space vehicle that re-enters an atmosphere. The structure has a fore-body, an aft-body, a longitudinal axis and a transverse cross sectional shape, projected on a plane containing the longitudinal axis, that includes: first and second linear segments, smoothly joined at a first end of each the first and second linear segments to an end of a third linear segment by respective first and second curvilinear segments; and a fourth linear segment, joined to a second end of each of the first and second segments by curvilinear segments, including first and second ellipses having unequal ellipse parameters. The cross sectional shape is non-symmetric about the longitudinal axis. The fourth linear segment can be replaced by a sum of one or more polynomials, trigonometric functions or other functions satisfying certain constraints.

摘要翻译： 用于增强空气动力性能的凸壳结构和/或重新进入气氛的空间车辆的传热要求降低。 该结构具有突出在包含纵向轴线的平面上的前体，后体，纵向轴线和横截面形状，其包括：第一和第二线性段，在每个的第一端处平滑地接合 第一和第二线性段通过相应的第一和第二曲线段到达第三线性段的端部; 以及第四线性段，其通过曲线段连接到每个第一和第二段的第二端，包括具有不等椭圆参数的第一和第二椭圆。 横截面形状关于纵向轴线是不对称的。 第四线性段可以由一个或多个多项式，三角函数或满足某些约束的其他函数的和代替。