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1. 发明公开

US20240239521A1 OPTIMISED STRUCTURE FOR REGULATING HEAT VIA HEAT PIPE FOR ELECTRONIC EQUIPMENT SUPPORT PANELS 审中-公开
公开(公告)号：US20240239521A1
公开(公告)日：2024-07-18
申请号：US18564970
申请日：2022-05-31
申请人： SONACA S.A.
发明人： Barbara MABED , Marc BEKEMANS
IPC分类号： B64G1/50 , H05K7/20
CPC分类号： B64G1/506 , H05K7/20336
摘要： A profile section for an equipment support panel. The profile section is formed in one piece, comprising a tube suitable for forming a heat pipe by introducing and confining a heat-transfer fluid inside of same, and a groove provided to form a rail along its length for securing at least one piece of equipment supported by the panel, this groove being shaped to form-fittingly engage with an attachment member rigidly connected to the at least one piece of equipment.

2. 发明授权

US11807403B2 Method of operating a spacecraft radiator panel 有权
公开(公告)号：US11807403B2
公开(公告)日：2023-11-07
申请号：US17180615
申请日：2021-02-19
申请人： Maxar Space LLC
发明人： Jason J. Chiang , Gordon Wu
IPC分类号： B64G1/10 , B64G1/50 , B64G1/58
CPC分类号： B64G1/58 , B64G1/10 , B64G1/503 , B64G1/506
摘要： Techniques for minimizing diurnal temperature variation of a radiator of a spacecraft are disclosed. In one aspect, a spacecraft includes a body, a radiator panel, and a heat dissipating unit thermally coupled with the radiator panel. The spacecraft is configured to operate in an orbital plane, and has a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane, and a roll axis orthogonal to the pitch axis and the yaw axis. The radiator panel includes a surface area external to a body of the spacecraft, a first portion of the surface area facing a first direction that is substantially parallel to the roll axis, and a second portion of the surface area facing a second direction that has a substantial component parallel to the yaw axis.

3. 发明授权

US10837712B1 Multi-bore constant conductance heat pipe for high heat flux and thermal storage 有权
公开(公告)号：US10837712B1
公开(公告)日：2020-11-17
申请号：US15093428
申请日：2016-04-07
申请人： ADVANCED COOLING TECHNOLOGIES, INC.
发明人： Michael Dechristopher , William G. Anderson , Jens E. Weyant , Calin Tarau , Andrew J. Slippey
IPC分类号： F28D15/00 , F28D15/02 , F28D15/04 , F28F1/40 , F28D20/02 , B64G1/50
CPC分类号： F28D15/0266 , B64G1/506 , F28D15/0233 , F28D15/0275 , F28D15/046 , F28D20/021 , F28F1/40
摘要： A heat pipe device comprising at least two of the following: an axially grooved bore for thermal transport, the axially grooved bore having an axial groove wick; a phase change material bore for thermal storage, the phase change material bore having internal fins to enhance heat transfer, the internal fins extend along the axis of the phase change material bore; and a porous media bore for accepting high heat fluxes, the porous media bore having a porous media wick in areas of high heat flux.

4. 发明申请

US20180273215A1 ELECTRIC THRUSTER WASTE HEAT RECOVERY DURING SATELLITE ORBIT TRANSFER 审中-公开
公开(公告)号：US20180273215A1
公开(公告)日：2018-09-27
申请号：US15470592
申请日：2017-03-27
申请人： Space Systems/Loral, LLC
发明人： Cameron Ground , Gordon Wu , Derek Chan
IPC分类号： B64G1/50 , B64G1/26 , B64G1/40 , B64G1/58 , F24F13/02
CPC分类号： B64G1/506 , B64G1/26 , B64G1/40 , B64G1/405 , B64G1/503 , B64G1/58 , F24F13/02
摘要： A spacecraft includes a spacecraft main body, including payload equipment disposed on an inner panel surface of at least one radiator panel, the at least one radiator panel having an exterior-facing outer panel surface. The spacecraft includes at least one electric thruster disposed proximate to an aft facing panel of the spacecraft main body. The at least one electric thruster is thermally coupled with the at least one radiator panel by way of a thermally conductive path.

5. 发明申请

US20180134416A1 Passive Thermal System Comprising Combined Heat Pipe and Phase Change Material and Satellites Incorporating Same 审中-公开
公开(公告)号：US20180134416A1
公开(公告)日：2018-05-17
申请号：US15870642
申请日：2018-01-12
申请人： WorldVu Satellites Limited
发明人： Alexander D. Smith , Daniel W. Field , Armen Askijian , James Grossman
IPC分类号： B64G1/50 , F28D15/04 , B64G1/10 , B64G1/40 , B64G1/28 , B64G1/26 , B64G1/66
CPC分类号： B64G1/50 , B64G1/10 , B64G1/26 , B64G1/283 , B64G1/40 , B64G1/402 , B64G1/503 , B64G1/506 , B64G1/66 , F28D15/0275 , F28D15/04 , F28D15/043 , F28D15/046 , F28D20/02 , F28D2020/0013 , F28F1/16 , F28F1/422 , F28F2013/006 , Y02E60/145
摘要： A passive thermal system for use in a satellite and other aerospace applications includes a container having a heat-pipe working fluid disposed in a first chamber and a Phase Change Material (PCM) disposed in a second chamber that substantially surrounds the first chamber. The first chamber contains a wick for transporting the heat-pipe working fluid. The exterior of the first chamber has fins, etc., that extend into the PCM for heat spreading and increased interface area.

6. 发明授权

US09868551B2 Passive thermal system comprising combined heat pipe and phase change material and satellites incorporating same 有权
公开(公告)号：US09868551B2
公开(公告)日：2018-01-16
申请号：US14673170
申请日：2015-03-30
申请人： WorldVu Satellites Limited
发明人： Alexander Smith , Daniel W. Field , Armen Askijian , James Grossman
IPC分类号： F28D15/00 , B64G1/50 , F28D15/04 , B64G1/10 , B64G1/26 , B64G1/28 , B64G1/40 , B64G1/66
CPC分类号： B64G1/50 , B64G1/10 , B64G1/26 , B64G1/283 , B64G1/40 , B64G1/402 , B64G1/503 , B64G1/506 , B64G1/66 , F28D15/0275 , F28D15/04 , F28D15/043 , F28D15/046 , F28D20/02 , F28D2020/0013 , F28F1/16 , F28F1/422 , F28F2013/006
摘要： A passive thermal system for use in a satellite and other aerospace applications includes a container having a heat-pipe working fluid disposed in a first chamber and a Phase Change Material (PCM) disposed in a second chamber that substantially surrounds the first chamber. The first chamber contains a wick for transporting the heat-pipe working fluid. The exterior of the first chamber has fins, etc., that extend into the PCM for heat spreading and increased interface area.

7. 发明申请

US20170328647A1 COMPOSITE HEAT PIPES AND SANDWICH PANELS, RADIATOR PANELS, AND SPACECRAFT WITH COMPOSITE HEAT PIPES 有权
公开(公告)号：US20170328647A1
公开(公告)日：2017-11-16
申请号：US15153386
申请日：2016-05-12
申请人： The Boeing Company
发明人： Richard W. Aston , Anna Maria Tomzynska
IPC分类号： F28D15/02 , B64G1/50 , F28D15/04 , B23P15/26
CPC分类号： F28D15/0275 , B23P15/26 , B64G1/503 , B64G1/506 , F28D15/04 , F28D2021/0021
摘要： Composite heat pipes, methods of assembling composite heat pipes, sandwich panels having one or more composite heat pipes, methods of assembling sandwich panels, radiator panels, methods of assembling radiator panels, spacecraft, and methods of assembling spacecraft are disclosed. Composite heat pipes include an elongate conductive casing and one or more fiber reinforced composite layers operatively coupled to one or more lateral sides of the elongate conductive casing. Sandwich panels include two spaced-apart face-sheets, a core positioned between the two spaced-apart face-sheets, and one or more composite heat pipes. Spacecraft include a body and two radiator panels operatively coupled to the body opposite each other.

8. 发明申请

US20170088294A1 CUBESAT FORM FACTOR THERMAL CONTROL LOUVERS 有权
公开(公告)号：US20170088294A1
公开(公告)日：2017-03-30
申请号：US14867896
申请日：2015-09-28
申请人： U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration
发明人： ALLISON L. WILLINGHAM
IPC分类号： B64G1/50 , E06B7/084
CPC分类号： B64G1/503 , B64G1/506
摘要： Thermal control louvers for CubeSats or small spacecraft may include a plurality of springs attached to a back panel of the thermal control louvers. The thermal control louvers may also include a front panel, which includes at least two end panels interlocked with one or more middle panels. The front panel may secure the springs, shafts, and flaps to the back panel.

9. 发明授权

US09352856B1 Axially grooved crossing heat pipes 有权
标题翻译：轴向沟槽交叉热管
公开(公告)号：US09352856B1
公开(公告)日：2016-05-31
申请号：US14097020
申请日：2013-12-04
申请人： Space Systems/Loral, LLC
发明人： Gordon Wu
IPC分类号： B64G1/52 , B64G1/50 , G01M17/00
CPC分类号： B64G1/503 , B64G1/1007 , B64G1/506 , G01M17/00
摘要： A spacecraft includes substantially parallel first radiator and second radiator panels, and a transverse panel coupled, having a width, W, coupled therebetween. The spacecraft also includes a first heat pipe having a first section parallel and proximate to the first radiator panel and a second section parallel and proximate to the transverse panel, a second heat pipe having a first section parallel and proximate to the second radiator panel and a second section parallel and proximate to the transverse panel and a third heat pipe, proximate and parallel to the transverse panel, the second section of the first heat pipe, and the second section of the second heat pipe. The third heat pipe has a length, L, substantially greater than W/2.
摘要翻译：航天器包括基本上平行的第一散热器和第二散热器面板，并且连接有宽度W的横向面板。航天器还包括第一热管，第一热管具有平行并靠近第一散热器面板的第一部分和平行并靠近横向面板的第二部分，第二热管具有平行并靠近第二散热器面板的第一部分，第二部分平行且靠近横向板，第三热管邻近并平行于横向板，第一热管的第二部分和第二热管的第二部分。第三热管的长度L大致大于W / 2。

10. 发明申请

US20160016678A1 SOLAR REJECTION SYSTEM WITH MOVABLE SUNSHADE 有权
标题翻译：具有可移动SUNSHADE的太阳能吸收系统
公开(公告)号：US20160016678A1
公开(公告)日：2016-01-21
申请号：US14799636
申请日：2015-07-15
申请人： RAYTHEON COMPANY
发明人： Andrew L. Bullard
IPC分类号： B64G1/54
CPC分类号： B64G1/546 , B64G1/503 , B64G1/506 , B64G1/54 , B64G1/58 , B64G1/66 , G03B11/045
摘要： A solar rejection system includes an enclosure for housing a sensor, and a movable sunshade. The housing has an opening or aperture for admitting light to the sensor, and the sunshade is moved as needed to prevent harmful solar illumination of the sensor. The sunshade may be a flat panel. The sunshade panel is mounted to a hinge that is located on one side of a large diameter bearing that allows the shade to be rotated around the aperture of the sensor to always prevent the sun from illuminating the aperture. The hinge allows the shade to be tilted to either allow the sensor to see further off axis without obscuration or to block the sun when it moves in front of the sensor. Full closure of the sunshade on its hinge allows it to also function as an aperture door, blocking the opening or aperture.
摘要翻译：太阳能排除系统包括用于容纳传感器的外壳和可移动的遮阳罩。壳体具有用于将光引导到传感器的开口或孔，并且遮阳板根据需要移动以防止传感器的有害的太阳照射。遮阳可以是平板。遮阳板安装在铰链上，该铰链位于大直径轴承的一侧，允许遮光罩围绕传感器的孔旋转，以防止太阳照射孔。铰链允许阴影倾斜，以允许传感器远离轴线而不会遮挡，或者在传感器前方移动时遮挡太阳。遮阳板在其铰链上的完全关闭允许其还用作孔门，阻挡开口或孔。

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