-
公开(公告)号：US10562647B2
公开(公告)日：2020-02-18
申请号：US15849289
申请日：2017-12-20
发明人： Andrew E. Turner
摘要： A spacecraft operating in a low earth orbit having an altitude in the range of 160 to 800 km has a main body that includes heat dissipating electrical equipment and an earth-facing payload. Control surfaces on the spacecraft are articulated so as to: provide three-axis attitude control to the spacecraft main body using aerodynamic drag effects, such that the earth-facing payload is maintained in a selected orientation with respect to the earth; and control one or both of orbit altitude and period by articulating the control surfaces so as to regulate an amount of aerodynamic drag. The control surfaces include a first control surface disposed, in an on-orbit configuration, on a boom, the boom being mechanically coupled with the main body, and with one or both of a solar array electrically coupled with the electrical equipment and a thermal radiating array thermally coupled with the electrical equipment.
-
公开(公告)号：US10538346B2
公开(公告)日：2020-01-21
申请号：US15470592
申请日：2017-03-27
发明人： Cameron Ground , Gordon Wu , Derek Chan
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.
-
公开(公告)号：US10207825B2
公开(公告)日：2019-02-19
申请号：US15108780
申请日：2014-12-24
发明人： Raphaël Hache , Bruno Trancart , Andrew Walker
摘要： A telecommunications satellite stabilized on three axes includes a set of dissipative equipment constituting a payload of the satellite. The satellite includes support data transmission antennas and is substantially parallelepipedal in shape with the panels forming two opposite faces, east and west faces. The panels form two additional opposite faces, north and south faces, and include radiator surfaces on their external faces. The radiator surfaces are configured to cool the electronic equipment of the satellite. The equipment installed on the north and south panels dissipate thermal power corresponding to less than 25% of the total dissipated power.
-
公开(公告)号：US20190023427A1
公开(公告)日：2019-01-24
申请号：US15654569
申请日：2017-07-19
申请人： The Boeing Company
发明人： Michael James Fuller , Daniel J. Leonard , John B. Lauger , Brian R. Dunaway , John Charles Gray
摘要： A temperature control system may include a heat exchanger configured to cool air within a pressurized enclosed crew cabin when the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger. The system may further include a sublimator configured to cool the coolant. The system may also include a primary coolant line configured to transport the coolant from the sublimator through the heat exchanger.
-
公开(公告)号：US20190016482A1
公开(公告)日：2019-01-17
申请号：US16133879
申请日：2018-09-18
发明人： Bruin Benthem
摘要： A radiator comprising at least one heat conductive layer having an in-plane heat conductivity of at least 500 W/mK and at least one heat emission layer in contact with the heat conductive layer, wherein the emission layer has an exposed surface with an emissivity of at least 0.7. Preferably, the heat conductive layer comprises a carbon-based material. The radiator is to be used in combination with a space vehicle structure, and due to its flexible character may be conformed to the particular shapes of such structure.
-
公开(公告)号：US10155597B2
公开(公告)日：2018-12-18
申请号：US15750980
申请日：2016-08-10
发明人： Philippe Cael , Andrew Walker , Fabrice Mena
摘要： Disclosed is an artificial satellite including one face from the North face and the South face supporting at least one main radiator having an outer face turned towards space and an inner face opposite the outer face. The satellite includes a bearing structure carrying the North face, the South face, the East face and the West face. At least one part of the at least one main radiator protrudes from at least one face from the East face and the West face. The inner face of the at least one protruding part is covered with a high infrared emissivity material. The value of the dimension of the at least one protruding part is between 19% and 50% of the value of the distance between the East and West faces.
-
27.发明申请公开(公告)号：US20180320983A1
公开(公告)日：2018-11-08
申请号：US15772444
申请日：2016-11-16
摘要： Disclosed is a heat exchange device for effecting a heat exchange between a heat transfer fluid of a first network of capillary heat pipes and a heat transfer fluid of a second network of capillary heat pipes. The heat exchange device includes a solid block provided with a first channel and a second channel which are independent of one another, the first channel having at least one opening intended to be connected to a capillary heat pipe of the first network, the second channel having at least one opening intended to be connected to a capillary heat pipe of the second network, the first channel having a portion which lies near a portion of the second channel such that the heat transfer fluid of the first network is able to exchange heat with the heat transfer fluid of the second network via the heat exchanging portions.
-
公开(公告)号：US10118717B2
公开(公告)日：2018-11-06
申请号：US15565703
申请日：2016-06-01
发明人： Andrew Walker
摘要： Disclosed is an artificial satellite including a battery pack capable of dissipating heat, at least one radiator capable of conveying the heat dissipated by the battery pack into space, and a low-dissipation equipment item having an individual power flux density of less than 250 watts/m2. The satellite includes a thermally insulating cover delimiting, together with the radiator, an interior isothermal zone in which thermal control takes place by radiation, the battery pack and the low-dissipation equipment being arranged in thermally insulating cover. The battery pack has an operating range of between 0° C. and 50° C. and preferably of between 10° C. and 30° C.
-
公开(公告)号：US20180273215A1
公开(公告)日：2018-09-27
申请号：US15470592
申请日：2017-03-27
发明人： Cameron Ground , Gordon Wu , Derek Chan
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.
-
公开(公告)号：US20180251238A1
公开(公告)日：2018-09-06
申请号：US15449368
申请日：2017-03-03
发明人： ALAN R. CHERRETTE
CPC分类号： B64G1/10 , B64G1/002 , B64G1/1007 , B64G1/443 , B64G1/503 , B64G1/64 , B64G1/641 , B64G2001/643 , H01Q1/288 , H01Q3/26 , H01Q15/16 , H01Q19/13 , H01Q19/19 , H01Q21/28
摘要： A three-axis spacecraft including a spacecraft body including first and second opposing radiator/equipment panels, first and second opposing mounting panels, an earth deck and a zenith deck. The zenith deck faces the Earth when the spacecraft is on orbit and the first and second mounting panels face an east and west direction relative to the Earth when the spacecraft is on orbit. The spacecraft further includes a mounting cylinder extending through the spacecraft body and out of the first and second mounting panels.
-
-
-
-
-
-
-
-
-
搜索结果
594 条记录 (耗时 0.096 秒)
