CN105636404A - Liquid cooling system for avionic device - Google Patents
Liquid cooling system for avionic device Download PDFInfo
- Publication number
- CN105636404A CN105636404A CN201410605271.XA CN201410605271A CN105636404A CN 105636404 A CN105636404 A CN 105636404A CN 201410605271 A CN201410605271 A CN 201410605271A CN 105636404 A CN105636404 A CN 105636404A
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- Prior art keywords
- liquid
- pump
- electronic equipment
- heat
- gas
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Abstract
The invention relates to a liquid cooling system for an avionic device, and the system is sequentially connected with a liquid pump (1), a liquid-liquid heat radiator (2), a gas-liquid separator (3) and electronic equipment (5) through a pipe (6). A conduit at the downstream side of the electronic equipment (5) is provided with a temperature sensor (4), and a controller (7) is enabled to be connected with the temperature sensor (4) and the liquid pump (1) through a control line. The gas-liquid separator (3) is disposed at the upstream side of the liquid pump (1). Compared with the prior art, the system is simple in construction, is stable and reliable in operation, does not need to punch an air inlet, and does not affect the pneumatic shape of an airplane. A conventional fuel oil system of an airplane serves as a heat sink, and the heat sink carries out heat exchange with the cooling liquid, thereby bringing away the heat generated by airborne electronic equipment. Meanwhile, a variable-frequency liquid pump is employed, and the rotating speed of the pump is automatically adjusted according to the liquid temperature of a pump inlet, so as to control the liquid supply temperature of the system, thereby achieving the optimal management of heat energy, and reducing the cost and loss of the airplane.
Description
Technical field
The invention belongs to plane environmental control system designing technique.
Background technology
Being take away electronic equipment thermal force by coolant mostly currently for liquid-cooling system high-power, high heat flux air environment, heat is taken to outside machine by recycling ram-air. This type of cooling needs substantial amounts of ram-air and coolant to carry out heat exchange, it is necessary to open ram intake on fuselage, has a strong impact on the aerodynamic configuration of aircraft, increases the panelty of aircraft.
Simultaneously, system supplies the control of liquid temp typically via two kinds of methods: be 1. that the flow regulating cold limit ram-air by regulating the aperture of MOD supplies liquid temp with control system, this temperature regulation mechanism is higher to the Structural strength calls of MOD and cold air duct, and the impact of aircraft panelty is bigger; 2. being that coolant is divided into two-way, a road and ram-air generation heat exchange form cold road, and a road direct circulation forms hot road, control system for liquid temp by regulating the flow-rate ratio on cold and hot road. This temperature regulation mechanism need nonetheless remain for certain ram-air, affects the aerodynamic configuration of aircraft equally, increases the panelty of aircraft.
Summary of the invention
Goal of the invention
The present invention utilizes fuel oil and coolant to carry out heat exchange, takes away the thermal force of air environment. Achieve the optimal management of heat energy, nonramming airscoop, do not affect Aerodynamic Configuration of Aireraft, decrease the panelty of aircraft.
Technical scheme
A kind of avionic device liquid-cooling system, it is sequentially connected with liquid pump 1, Liquid-liquid radiator 2, gas-liquid separator 3 and electronic equipment 5 by pipeline 6, the conduit in electronic equipment 5 downstream is provided with temperature sensor 4, being connected with temperature sensor 4 and liquid pump 1 by controller 7 by controlling circuit, wherein gas-liquid separator 3 is located at the upstream of liquid pump 1.
Described system is enclosed liquid circulation cooling system, liquid pump 1 provides circulation power for coolant flowing in system pipeline 6, coolant takes away, by cold drawing, the heat that electronic equipment 5 produces, subsequently into Liquid-liquid radiator 2 by fuel cools, gas-liquid separator 3 is for the bubble separated in coolant and balances the coolant change in volume caused because expanding with heat and contract with cold, controller 7 can be automatically adjusted the rotating speed of liquid pump 1 according to the temperature of liquid that pump intake fluid temperature sensor 4 is surveyed, to ensure the temperature stabilization of fluid circulation system.
Beneficial effect
Compared with prior art, simple structure of the present invention, working stability, reliable, it is not necessary to ram intake, do not affect Aerodynamic Configuration of Aireraft. Utilize the existing fuel system of aircraft as heat sink, by taking away heat produced by air environment with coolant heat exchange, adopt frequency conversion liquid pump simultaneously, it is automatically adjusted the rotating speed of pump to control the confession liquid temp of system according to pump intake temperature of liquid, achieve the optimal management of heat energy, reduce aircraft panelty.
Accompanying drawing explanation
Fig. 1 is present system operating diagram
Detailed description of the invention
Referring to Fig. 1, it is sequentially connected with liquid pump 1, Liquid-liquid radiator 2, gas-liquid separator 3 and electronic equipment 5 by pipeline 6, the conduit in electronic equipment 5 downstream is provided with temperature sensor 4, by controlling circuit, controller 7 is connected with temperature sensor 4 and liquid pump 1.
Adopt enclosed liquid circulation cooling system, liquid pump 1 provides circulation power for coolant flowing in system pipeline 6, coolant takes away, by cold drawing, the heat that electronic equipment 5 produces, subsequently into Liquid-liquid radiator 2 by fuel cools, the gas-liquid separator 3 arranged in system has the effect of gas-liquid separator and expansion tank concurrently, controller 7 can be automatically adjusted the rotating speed of liquid pump 1 according to the temperature of liquid that pump intake fluid temperature sensor 4 is surveyed, to ensure the temperature stabilization of fluid circulation system.
Claims (2)
1. an avionic device liquid-cooling system, it is characterized in that: described system is sequentially connected with liquid pump (1), Liquid-liquid radiator (2), gas-liquid separator (3) and electronic equipment (5) by pipeline (6), the conduit in electronic equipment (5) downstream is provided with temperature sensor (4), being connected with temperature sensor (4) and liquid pump (1) by controller (7) by controlling circuit, wherein gas-liquid separator (3) is located at the upstream of liquid pump (1).
2. a kind of avionic device liquid-cooling system as claimed in claim 1, it is characterized in that: described system is enclosed liquid circulation cooling system, liquid pump (1) provides circulation power for coolant flowing in system pipeline (6), coolant takes away, by cold drawing, the heat that electronic equipment (5) produces, subsequently into Liquid-liquid radiator (2) by fuel cools, gas-liquid separator (3) is for the bubble separated in coolant and balances the coolant change in volume caused because expanding with heat and contract with cold, controller (7) can be automatically adjusted the rotating speed of liquid pump (1) according to the temperature of liquid that pump intake fluid temperature sensor (4) are surveyed, to ensure the temperature stabilization of fluid circulation system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410605271.XA CN105636404A (en) | 2014-10-31 | 2014-10-31 | Liquid cooling system for avionic device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410605271.XA CN105636404A (en) | 2014-10-31 | 2014-10-31 | Liquid cooling system for avionic device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105636404A true CN105636404A (en) | 2016-06-01 |
Family
ID=56050728
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410605271.XA Pending CN105636404A (en) | 2014-10-31 | 2014-10-31 | Liquid cooling system for avionic device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105636404A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106659076A (en) * | 2016-12-15 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Split booster expansion device |
| CN111511173A (en) * | 2020-05-09 | 2020-08-07 | 陕西飞机工业（集团）有限公司 | Equipment cooling system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102390536A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Three-wheel pressure-boosting refrigerating and liquid cooling composite thermal energy managing system |
| WO2013133574A1 (en) * | 2012-03-06 | 2013-09-12 | Lee Ha Song | Electronic component cooling device built into aircraft |
| CN103561556A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Aeration-cooling method for avionic devices |
-
2014
- 2014-10-31 CN CN201410605271.XA patent/CN105636404A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102390536A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Three-wheel pressure-boosting refrigerating and liquid cooling composite thermal energy managing system |
| WO2013133574A1 (en) * | 2012-03-06 | 2013-09-12 | Lee Ha Song | Electronic component cooling device built into aircraft |
| CN103561556A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Aeration-cooling method for avionic devices |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106659076A (en) * | 2016-12-15 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Split booster expansion device |
| CN111511173A (en) * | 2020-05-09 | 2020-08-07 | 陕西飞机工业（集团）有限公司 | Equipment cooling system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160601 |
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| WD01 | Invention patent application deemed withdrawn after publication |