公开(公告)号：US06260798B1

公开(公告)日：2001-07-17

申请号：US09425609

申请日：1999-10-22

申请人： Thierry Casiez ,  Carlos Cesnik ,  Mark Drela ,  Staci N. Jenkins ,  Mark Spearing

发明人： Thierry Casiez ,  Carlos Cesnik ,  Mark Drela ,  Staci N. Jenkins ,  Mark Spearing

IPC分类号： B64C338

CPC分类号： B64F1/04 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  Y02T50/14

摘要： A compact, aerodynamic wing assembly constructed and arranged so as to withstand a force due to acceleration in at least one direction includes at least two wing segments, each of the wing segments having a span-wise axis, and a airfoil cross section normal to the span axis. The wing segments are preferably disposed mutually adjacent and end to end. For each pair of wing segments, the wing further includes a pivot assembly fixedly attached to the wing segments at an end of each of the wing segments along the span-wise axis. The pivot assembly forms an articulation axis for relative movement between each the pair of wing segments, such that the wing assembly converts, upon a predetermined stimulus, from a stowed configuration characterized by nested wing segments, to a deployed configuration characterized by a substantially uninterrupted aerodynamic surface. The wing assembly is preferably constructed and arranged to withstand forces due to acceleration in at least two directions, including 15,000 g's forward and 4,000 g's rebound accelerations. The invention further comprises a flying structure constructed and arranged so as to withstand an acceleration force directed along a main axis. The flying structure includes a body disposed about the main axis, and at least one wing assembly pivotally mounted to the body. The wing assembly is constructed and arranged so as to convert, upon a predetermined stimulus, from a stowed configuration characterized by nested wing segments, to a deployed configuration characterized by a substantially uninterrupted aerodynamic surface.

摘要翻译： 构造和布置为承受由于至少一个方向上的加速度而产生的力的紧凑的空气动力学翼组件包括至少两个翼段，每个翼段具有跨度轴线，并且翼型横截面垂直于 跨度轴。 翼片段优选地彼此相邻并且端对端设置。 对于每对翼段，机翼还包括枢转组件，该枢轴组件沿翼展轴线固定地连接到每个翼片段的端部处的翼段。 枢轴组件形成用于每对翼段之间的相对运动的铰接轴线，使得翼组件在预定的刺激下将由嵌套的翼片段特征的收起构型转换成展开的构型，其特征在于基本上不间断的空气动力学 表面。 翼组件优选地构造和布置成承受由于至少两个方向上的加速的力，包括15,000g的向前和4,000g的回弹加速度。 本发明还包括一个构造和布置以便承受沿主轴定向的加速力的飞行结构。 飞行结构包括围绕主轴设置的主体，以及枢转地安装到主体的至少一个翼组件。 机翼组件被构造和布置成在预定的刺激下从由特征为嵌套的翼段的收起构型转换到特征在于基本上不间断的空气动力学表面的展开构型。