公开(公告)号：US06378809B1

公开(公告)日：2002-04-30

申请号：US09154396

申请日：1998-09-16

申请人： Randy Pon

发明人： Randy Pon

IPC分类号： B64G122

CPC分类号： B64G1/503

摘要： In a presently preferred embodiment of this invention a spacecraft includes at least four thermal radiator panels, with a first pair of said panels being initially stowed along a North facing surface of said spacecraft and a second pair of said panels being initially stowed along a South facing surface of said spacecraft. Each of said panels is coupled to a hinge mechanism at an anti-Earth facing end of said spacecraft and is rotatable by said hinge mechanism from a stowed position to a deployed position. The deployed position is a position that is off of the anti-Earth facing end of the spacecraft. In the presently preferred embodiment of this invention, when in the deployed position a longitudinal axis of each of said panels forms a non-zero angle with an Earth-pointing axis of said spacecraft.

摘要翻译： 在本发明目前优选的实施例中，航天器包括至少四个散热器散热器板，其中第一对所述面板最初沿着所述航天器的朝北表面收起，并且第二对所述面板最初沿着南面 所述航天器的表面。 每个所述面板在所述航天器的反地球面端处联接到铰链机构，并且可由所述铰链机构从收起位置旋转到展开位置。 展开位置是离开飞船的反地球端的位置。 在本发明的当前优选实施例中，当处于展开位置时，每个所述面板的纵向轴线与所述航天器的地球轴线形成非零角度。

公开(公告)号：US07363960B2

公开(公告)日：2008-04-29

申请号：US09822073

申请日：2001-03-30

申请人： Lenny Low ,  Randy Pon

发明人： Lenny Low ,  Randy Pon

IPC分类号： F28F7/00

CPC分类号： F28D15/0241 ,  B64G1/503 ,  B64G1/506 ,  F28D15/0266

摘要： Heat transfer systems and methods 30 for use on a spacecraft that use a loop heat pipe to transfer heat from a remotely located heat source to a thermal radiator or other heat dissipating apparatus. The loop heat pipe is a two phase heat transfer device that has an evaporator coupled to the heat source and a condenser coupled to the thermal radiator or other heat dissipating apparatus. The loop heat pipe comprises thin walled tubing to connect the evaporator and condenser. The thin walled tubing allows the loop heat pipe to be flexible. This flexibility offers significant advantages in terms of routing and accommodating design

摘要翻译： 用于航天器的传热系统和方法30，其使用环形热管将热量从远程定位的热源传递到散热器或其它散热装置。 回路热管是两相传热装置，其具有耦合到热源的蒸发器和耦合到散热器或其它散热装置的冷凝器。 回路热管包括连接蒸发器和冷凝器的薄壁管。 薄壁管道允许回路热管柔性。 这种灵活性在路由和容纳设计方面提供了显着的优势

公开(公告)号：US06883588B1

公开(公告)日：2005-04-26

申请号：US09624151

申请日：2000-07-24

申请人： Lenny Low ,  Randy Pon

发明人： Lenny Low ,  Randy Pon

IPC分类号： B64G1/50 ,  F24F5/00 ,  F25B9/00 ,  F25B27/00 ,  F28D15/00 ,  F25B13/00

CPC分类号： F25B27/005 ,  B64G1/50 ,  B64G1/503 ,  B64G1/506 ,  F25B9/002 ,  Y02A40/966

摘要： Heat dissipating apparatus or system for dissipating heat generated by a payload on a spacecraft having a plurality of surfaces. The system includes at least one radiator-condenser coupled to one or more of the surfaces of the spacecraft and a heat pump including an evaporator, a compressor, and an expansion valve coupled in a closed-loop manner to the radiator-condenser. The system components are coupled together using small diameter, thin- and smooth-walled tubing. The system enables the radiator-condenser to be elevated above the source or payload temperature, and, along with the use of thin walled tubing, reduces the mass of the spacecraft. Because the radiator-condenser temperatures are elevated, multiple surfaces of the spacecraft (west, east, earth and aft) can be effectively used as radiating surfaces.

摘要翻译： 用于耗散由具有多个表面的航天器上的有效载荷产生的热的散热装置或系统。 该系统包括耦合到航天器的一个或多个表面的至少一个散热器 - 冷凝器，以及包括蒸发器，压缩机和以闭环方式耦合到散热器 - 冷凝器的膨胀阀的热泵。 系统部件使用小直径，薄壁和平滑的管道连接在一起。 该系统使散热器 - 冷凝器升高到源或有效载荷温度以上，并且与使用薄壁管一起降低了航天器的质量。 由于散热器 - 冷凝器的温度升高，所以航天器的多个表面（西，东，土，船尾）可以有效地用作辐射表面。