Variable heat rejection using heat pipe heat exchanger
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F28F-027/00
G05D-016/00
G05D-023/00
F28D-015/02
B64G-001/50
출원번호
US-0739364
(2015-06-15)
등록번호
US-9939203
(2018-04-10)
발명자
/ 주소
Cho, Wei-Lin
Adamson, Gary A.
출원인 / 주소
HAMILTON SUNDSTRAND CORPORATION
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
9
초록▼
A system according to an exemplary aspect of the present disclosure includes, among other things, a control unit and a heat pipe heat exchanger having a first heat pipe and a second heat pipe. The system also includes a first flow regulator selectively adjustable in response to instructions from the
A system according to an exemplary aspect of the present disclosure includes, among other things, a control unit and a heat pipe heat exchanger having a first heat pipe and a second heat pipe. The system also includes a first flow regulator selectively adjustable in response to instructions from the control unit to direct a first flow of fluid over a portion of the first heat pipe. Further, the system includes a second flow regulator selectively adjustable in response to instructions from the control unit to direct a second flow of fluid over a portion of the second heat pipe. A method is also disclosed.
대표청구항▼
1. A system, comprising: a control unit;a heat pipe heat exchanger, a first heat exchanger, a second heat exchanger, a plurality of first heat pipes having first and second ends, and a plurality of second heat pipes having first and second ends;where the first ends of the first heat pipes project in
1. A system, comprising: a control unit;a heat pipe heat exchanger, a first heat exchanger, a second heat exchanger, a plurality of first heat pipes having first and second ends, and a plurality of second heat pipes having first and second ends;where the first ends of the first heat pipes project into the first heat exchanger, where the first ends of the second heat pipes project into the second heat exchanger, and where the second ends of the first and second heat pipes project into the heat pipe heat exchanger;a first valve selectively adjustable in response to instructions from the control unit to direct a first flow of fluid to the first heat exchanger; anda second valve selectively adjustable in response to instructions from the control unit to direct a second flow of fluid to the second heat exchanger;wherein the first heat exchanger further includes a first set of valves, wherein each valve of the first set of valves is fluidly located between the first ends of two adjacent first heat pipes, wherein the valves of the first set of valves are fluidly arranged in series with respect to each other, and wherein the valves of the first set of valves are adjustable in response to instructions from the control unit to selectively direct fluid in series over the first ends of the first heat pipes, wherein the second heat exchanger further includes a second set of valves, wherein each valve of the second set of valves is fluidly located between the first ends of two adjacent second heat pipes, wherein the valves of the second set of valves are fluidly arranged in series with respect to each other, and wherein the valves of the second set of valves are adjustable in response to instructions from the control unit to selectively direct fluid in series over the first ends of the second plurality of heat pipes. 2. The system as recited in claim 1, wherein the first and second heat exchangers are arranged in parallel to one another. 3. The system as recited in claim 1, wherein the heat pipe heat exchanger is arranged to expose each of the first and second heat pipes to an external environment. 4. The system as recited in claim 3, wherein: the system is embodied on a spacecraft and the external environment is outer space;the control unit is electrically coupled to at least one sensor configured to generate a signal indicative of conditions within the spacecraft; andthe control unit is configured to selectively adjust the first and second sets of valves based on the conditions within the spacecraft. 5. The system as recited in claim 4, wherein: the control unit is electrically coupled to at least one sensor configured to generate a signal indicative of the conditions external to the spacecraft; andthe control unit is configured to selectively adjust the first and second sets of valves based on the conditions outside the spacecraft. 6. A system, comprising: a control unit;a heat pipe heat exchanger, a first heat exchanger having a plurality of first heat exchange portions, a second heat exchanger having a plurality of second heat exchange portions, a plurality of first heat pipes having first and second ends, and a plurality of second heat pipes having first and second ends;wherein the first ends of the first heat pipes each project into a respective first heat exchange portion of the first heat exchange portions, where the first ends of the second heat pipes each project into a respective second heat exchange portion of the second heat exchange portions, and where the second ends of the first and second heat pipes project into the heat pipe heat exchanger;a first valve selectively adjustable in response to instructions from the control unit to direct a first flow of fluid to the first heat exchanger; anda second valve selectively adjustable in response to instructions from the control unit to direct a second flow of fluid to the second heat exchanger;wherein the first heat exchanger further includes a first set of valves, wherein each valve of the first set of valves is fluidly connected to a respective first heat exchange portion of the plurality of first heat exchange portions, wherein the valves of the first set of valves are fluidly arranged in parallel with respect to each other, and wherein the valves of the first set of valves are adjustable in response to instructions from the control unit to selectively direct fluid in parallel over the first ends of the first heat pipes, wherein the second heat exchanger further includes a second set of valves, wherein each valve of the second set of valves is fluidly connected to a respective second heat exchange portion of the plurality of second heat exchange portions, wherein the valves of the second set of valves are fluidly arranged in parallel with respect to each other, and wherein the valves of the second set of valves are adjustable in response to instructions from the control unit to selectively direct fluid in parallel over the first ends of the second heat pipes.
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이 특허에 인용된 특허 (9)
Basuthakur Sibnath ; Allen Robert David ; Miller Daniel David, Active spacecraft thermal control system and method.
Blackmon James B. (Irvine CA) Drubka Robert E. (Huntington Beach CA) Kirby John S. (Long Beach CA) Johnson Dave (Riverside CA) Gerrick R. Andrew (Santa Ana CA) Ingersoll Thomas (Laguna Niguel CA) Jon, Advanced survivable radiator.
Gunnerson Fred S. (Oviedo FL) Sanderlin F. Dave (Lakeland FL) Iurato Joy R. (Tampa FL) Padilla Antonio A. (Tampa FL), Controllable heat pipes for thermal energy transfer.
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