公开(公告)号：US07055307B2

公开(公告)日：2006-06-06

申请号：US10930881

申请日：2004-08-31

Applicant: Edward James Wehner

Inventor： Edward James Wehner

IPC: F02K1/00

CPC classification number: F02K1/006 ,  F05D2250/411

Abstract: A vectorable nozzle includes a longitudinally extending upper fixed wall spaced upwardly and aftwardly of a longitudinally extending lower fixed wall and an aftwardly swept fixed ramp extending between the upper and lower fixed walls. The upper and lower fixed walls and the fixed ramp extend transversely between first and second fixed sidewalls. An outer nozzle wall is spaced apart from the upper and lower fixed walls and extends transversely between first and second fixed sidewalls. A nozzle flowpath is defined between the upper and lower fixed walls and the outer nozzle wall and the first and second fixed sidewalls. A sideways pivotable ramp structure pivotally connected to the lower fixed wall and pivotable between the sidewalls includes a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls.

Abstract translation: 可向导的喷嘴包括纵向延伸的上固定壁，其在纵向延伸的下固定壁和在上固定壁和下固定壁之间延伸的向后扫掠的固定斜面向上和向后间隔开。 上固定壁和固定斜面在第一和第二固定侧壁之间横向延伸。 外部喷嘴壁与上固定壁和下固定壁间隔开并在第一和第二固定侧壁之间横向延伸。 在上下固定壁和外喷嘴壁以及第一和第二固定侧壁之间限定喷嘴流路。 可枢转地连接到下固定壁并可在侧壁之间枢转的侧向可枢转斜面结构包括纵向延伸的上部可枢转壁，该纵向延伸的上部可枢转壁在纵向延伸的下部可枢转壁和在上部和下部可枢转壁之间延伸的向后扫掠的可枢转斜面之间向上和向后间隔开。

公开(公告)号：US20050263648A1

公开(公告)日：2005-12-01

申请号：US11044550

申请日：2005-01-27

Applicant: James Wehner ,  Christian Harris ,  Michael O'Rell

Inventor： James Wehner ,  Christian Harris ,  Michael O'Rell

IPC: B64G1/24 ,  B64G1/40 ,  B64G1/50 ,  B64G1/58 ,  B64G1/46

CPC classification number: B64G1/24 ,  B64G1/407 ,  B64G1/503 ,  B64G1/58

Abstract: A spacecraft including control vanes for controlling the pointing direction of the spacecraft by providing a variable absorptive, reflective, emissive and/or transmissive properties. The control vanes provide a torque on the spacecraft to maintain the spacecraft pointing towards the sun. The control vanes can include at least one xb-axis control vane and at least one yb-axis control vane where the xb axis control vane provides xb-axis control torque on the spacecraft rotated about the xb-axis, and the yb-axis control vane provides yb-axis control torque on the spacecraft when rotated about the yb-axis.

Abstract translation: 包括用于通过提供可变的吸收性，反射性，发射性和/或透射特性来控制航天器的指向方向的控制翼片的航天器。 控制叶片在航天器上提供扭矩，以保持航天器指向太阳。 控制叶片可以包括至少一个x轴控制叶片和至少一个轴向控制叶片，其中x B轴 控制叶片在围绕x轴旋转的航天器上提供x轴控制扭矩，并且控制叶片提供 在绕y轴转动的情况下，航天器的转矩控制转矩。

公开(公告)号：US20050263647A1

公开(公告)日：2005-12-01

申请号：US11044308

申请日：2005-01-27

Applicant: James Wehner ,  Christian Harris ,  Michael O'Rell

Inventor： James Wehner ,  Christian Harris ,  Michael O'Rell

IPC: B64G1/24 ,  B64G1/40 ,  B64G1/50 ,  B64G1/58 ,  B64G1/36

CPC classification number: B64G1/24 ,  B64G1/407 ,  B64G1/503 ,  B64G1/58

Abstract: Controlling the solar torque imposed on a spacecraft (10) in flight by providing a film (52) with variable absorptive, reflective, emissive and/or transmissive properties on the sun side of a thermal shield (50) of the spacecraft (10). As the orientation of the thermal shield (50) changes relative to the sun line, the absorptive, reflective, emissive and/or transmissive properties of the shield (50) change to cause the shield's (50) center of solar pressure to change, thus aligning it with the spacecraft (10) center of mass (24) as viewed from the direction of the sun line. In accordance with another embodiment of the invention, the spacecraft (100) is provided with a plurality of control vanes (110-116) that have a variable absorptive, transmissive, reflective and emissive property to maintain the spacecraft (100) stably pointed towards the sun.

Abstract translation: 通过在太空飞船（10）的热屏蔽（50）的太阳侧上提供具有可变吸收，反射，发射和/或透射特性的薄膜（52）来控制飞行中施加在航天器（10）上的太阳能转矩。 随着热屏蔽（50）的取向相对于太阳线变化，屏蔽（50）的吸收，反射，发射和/或透射特性改变，从而使屏蔽（50）的太阳压力中心发生变化，因此 将其与太阳线方向观察时的航天器（10）质心（24）对准。 根据本发明的另一个实施例，航天器（100）设置有多个控制叶片（110-116），其具有可变的吸收性，透射性，反射性和发射性，以将航天器（100）稳定地朝向 太阳。

公开(公告)号：US07096662B2

公开(公告)日：2006-08-29

申请号：US10952118

申请日：2004-09-28

Applicant: Edward James Wehner

Inventor： Edward James Wehner

IPC: F02K1/00

CPC classification number: F02K1/04 ,  F02K1/006 ,  F02K1/085

Abstract: A nozzle includes a sideways split and aftwardly swept nozzle ramp extends between a fixed lower nozzle wall and a pivotal upper nozzle wall pivotally connected to an aft end of the nozzle and operable to vary a throat area of a throat of the nozzle. The upper and lower nozzle walls and the ramp extend transversely between first and second nozzle sidewalls. A sideways pivotable ramp structure pivotally connected to the lower nozzle wall and pivotable between the sidewalls includes a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls. Right hand and left hand upper ramp sections of the nozzle ramp may be connected to right hand and left hand upper nozzle wall sections respectively of the upper nozzle wall which are pivotally connected to right and left handed triangular side walls of the aft end.

Abstract translation: 喷嘴包括侧向分开的和后掠的喷嘴斜面，其在固定的下喷嘴壁和可枢转地连接到喷嘴的后端的可枢转的上喷嘴壁之间延伸，并且可操作以改变喷嘴的喉部的喉部区域。 上下喷嘴壁和斜坡在第一和第二喷嘴侧壁之间横向延伸。 可枢转地连接到下喷嘴壁并且可在侧壁之间枢转的侧向可枢转斜面结构包括纵向延伸的上部可枢转壁，该纵向延伸的上部可枢转壁在纵向延伸的下部可枢转壁和在上部和下部可枢转壁之间延伸的向后扫掠的可枢转斜面之间向上和向后间隔开。 喷嘴斜面的右手和左手上坡道部分可以分别连接到上端喷嘴壁的左右上喷嘴壁部分，该上喷嘴壁部分枢转地连接到后端的左右三角形侧壁。

公开(公告)号：US07980514B2

公开(公告)日：2011-07-19

申请号：US12048981

申请日：2008-03-14

Applicant: James Wehner ,  Lael Rudd ,  Christian Harris ,  Shahram Foroozan

Inventor： James Wehner ,  Lael Rudd ,  Christian Harris ,  Shahram Foroozan

IPC: B64G1/24 ,  B64G1/44

CPC classification number: B64G1/506 ,  B64G1/283 ,  B64G1/285 ,  B64G1/407 ,  B64G1/428 ,  B64G1/44 ,  B64G1/443 ,  B64G1/66 ,  Y10S136/292

Abstract: One embodiment of the invention includes a spacecraft. The spacecraft comprises at least one solar array panel comprising an array of solar cell sections. Each of the solar cell sections can be configured to generate electrical power from received solar radiation. The spacecraft also comprises a solar array selection controller configured to selectively deactivate a portion of the array of solar cell sections to generate a torque on the spacecraft based on a difference in at least one of solar and thermal radiation pressure between an activated portion of the array of solar cell sections and the deactivated portion of the array of solar cell sections.

Abstract translation: 本发明的一个实施例包括一个航天器。 宇宙飞船包括至少一个包括太阳能电池部分阵列的太阳能阵列面板。 每个太阳能电池部分可被配置为从接收的太阳辐射产生电力。 航天器还包括太阳能阵列选择控制器，该太阳能阵列选择控制器被配置为基于在阵列的激活部分之间的太阳能和热辐射压力中的至少一个的差异来选择性地停用太阳能电池部分阵列的一部分以在航天器上产生扭矩 的太阳能电池部分和太阳能电池部分阵列的失活部分。

公开(公告)号：US20090230250A1

公开(公告)日：2009-09-17

申请号：US12048981

申请日：2008-03-14

Applicant: James Wehner ,  Lael Rudd ,  Christian Harris ,  Shahram Foroozan

Inventor： James Wehner ,  Lael Rudd ,  Christian Harris ,  Shahram Foroozan

IPC: B64G1/44

CPC classification number: B64G1/506 ,  B64G1/283 ,  B64G1/285 ,  B64G1/407 ,  B64G1/428 ,  B64G1/44 ,  B64G1/443 ,  B64G1/66 ,  Y10S136/292

Abstract: One embodiment of the invention includes a spacecraft. The spacecraft comprises at least one solar array panel comprising an array of solar cell sections. Each of the solar cell sections can be configured to generate electrical power from received solar radiation. The spacecraft also comprises a solar array selection controller configured to selectively deactivate a portion of the array of solar cell sections to generate a torque on the spacecraft based on a difference in at least one of solar and thermal radiation pressure between an activated portion of the array of solar cell sections and the deactivated portion of the array of solar cell sections.

Abstract translation: 本发明的一个实施例包括一个航天器。 宇宙飞船包括至少一个包括太阳能电池部分阵列的太阳能阵列面板。 每个太阳能电池部分可被配置为从接收的太阳辐射产生电力。 航天器还包括太阳能阵列选择控制器，该太阳能阵列选择控制器被配置为基于在阵列的激活部分之间的太阳能和热辐射压力中的至少一个的差异来选择性地停用太阳能电池部分阵列的一部分以在航天器上产生扭矩 的太阳能电池部分和太阳能电池部分阵列的失活部分。