阅读说明：本技术 一种星上大功率密度单机流体回路辐射器 (High power density single machine fluid circuit radiator on a kind of star ) 是由 马二瑞 蒋桂忠 林士峰 蒋国伟 张磊 任烜 张筱娴 许红阳 于 2019-09-23 设计创作，主要内容包括：本发明涉及一种星上大功率密度单机流体回路辐射器,包括蜂窝板、流体管道、散热单元和均热单元,所述蜂窝板为中空结构,所述流体管道固定设置在蜂窝板内,所述散热单元固定在蜂窝板面向环境的一侧,并用于将蜂窝板的热量传递给环境；所述均热单元固定在蜂窝板背向环境的一侧,并用于蜂窝板的等温化。本发明的辐射器具有散热能力强、占用空间小、工艺简单、稳定性良好、安全可靠等优点。(The present invention relates to high power density single machine fluid circuit radiators on a kind of star, including cellular board, fluid line, heat-sink unit and equal hot cell, the cellular board is hollow structure, the fluid line is fixed in cellular board, the heat-sink unit is fixed on the side of cellular board Environment Oriented, and is used for the heat transfer of cellular board to environment；The equal hot cell is fixed on side of the cellular board backwards to environment, and is used for the isothermal of cellular board.Radiator of the invention has many advantages, such as that heat-sinking capability is strong, occupies little space, simple process, have good stability, is safe and reliable.)

1. high power density single machine fluid circuit radiator on a kind of star, which is characterized in that the radiator includes cellular board, stream Body pipeline, heat-sink unit and equal hot cell, the cellular board are hollow structure, and the fluid line is fixed at cellular board Interior, the heat-sink unit is fixed on the side of cellular board Environment Oriented, and is used for the heat transfer of cellular board to environment；It is described Equal hot cell is fixed on side of the cellular board backwards to environment, and is used for the isothermal of cellular board.

2. high power density single machine fluid circuit radiator on star as described in claim 1, which is characterized in that the fluid hose Road disk-shaped distribution in cellular board.

3. high power density single machine fluid circuit radiator on star as claimed in claim 1 or 2, which is characterized in that the stream Fin is arranged in the two sides of body pipeline.

4. high power density single machine fluid circuit radiator on star as described in claim 1, which is characterized in that the heat dissipation is single Member is the silver-plated second surface mirror of cerium glass.

5. high power density single machine fluid circuit radiator on star as described in claim 1 or 4, which is characterized in that described to dissipate Hot cell is fixed on the side of cellular board Environment Oriented by way of bonding.

6. high power density single machine fluid circuit radiator on star as described in claim 1, which is characterized in that the soaking list Member is samming heat pipe, and the samming heat pipe and fluid line arranged crosswise.

7. high power density single machine fluid circuit radiator on star as described in claim 1, which is characterized in that the cellular board Material be aluminium.

Technical field

The present invention relates to AEROSPACE APPLICATION technical fields, and in particular to high power density single machine fluid circuit radiation on a kind of star Device.

Background technique

The purpose of satellite thermal control technology is control inside satellite and external environment heat exchanging process, realizes that on-board equipment heat is flat Weighing apparatus temperature is in claimed range.Thermal control technology is the important component of space technology, and design level and quality influence Working condition, service life and the reliability of entire satellite.With the continuous development of space technology, the application range of satellite gradually expands Greatly, on star payload because function difference it is multifarious, therefore satellite thermal control technology is constantly faced with new challenges.

Wherein, biggish heat consumption will be generated when high power density single machine is operated at full capacity on star, thermal control design necessarily encounters The quick transmitting of big heat and dissipation problem.For such problem, existing method mainly has adopting heat pipes for heat transfer system, monophasic fluid Loop cooling system and two-phase fluid loop cooling system.Wherein, Fluid for Single-phase Fluid Loop System cooling system it is strong with its heat transfer property, can It is concerned by the advantages that property height and simple process.Fluid for Single-phase Fluid Loop System cooling system is by Fluid for Single-phase Fluid Loop System and radiator group At the former can realize the quick transmitting of big heat, and the latter then realizes the efficient heat extraction to space environment.And the design of radiator exists While considering single machine radiating requirements, also to reduce its volume and weight as far as possible, reduce launch cost.Currently, radiator The mainstream shape of design has cylinder-shaped radiator, the single side wing-tubular type radiator, the flat radiator of rectangular conduit and pipeline-rib Chip radiator.

Cylinder-shaped radiator is mainly used in the temperature control system of international space station and Large Spacecraft.The system is to navigate The cylindrical wall of its device is coiled in the outer surface of radiator, passes through fluid circuit and spoke as radiator, fluid circuit pipeline The direct thermal coupling of emitter reduces thermal resistance, realizes the efficient heat transfer to spacecraft and accurate temperature control.The design of this radiator is suitable The larger and relatively regular shape spacecraft for body surface area.

The single side wing-tubular type radiator is mainly used in the thermal control design of space shuttle, using the covering of space shuttle as Radiating surface, the flow duct of cooling fluid are directly welded in space shuttle covering inner surface.This structure process is simple, weight It is small, high reliablity.But there is also certain disadvantages for the single side wing-tubular type radiator: radiator is thermally conductive with space shuttle covering It will affect the heat-sinking capability of system；And the transverse direction of covering is thermally conductive poor, causes radiator surface there are biggish temperature gradient, Influence the radiating efficiency of radiator.

The flat radiator of rectangular conduit is made of many flat rectangular conduits, and the top and bottom of conduit or one side are made For radiative heat rejection face.Heat transfer efficiency between the radiator and fluid is very high, and the temperature uniformity of plate radiating surface is preferable, can To realize the efficient heat extraction to space environment.Meanwhile except the flat radiator of rectangular conduit is independently of the structure of spacecraft, because This its occupied space is larger, and weight demands improve.And the conduit in the radiator is more, and runner design is complicated, process implementing Difficulty increases, and reliability reduces.

Pipeline-rib-type radiator is made of multiple pipelines-fin unit, the top and bottom of pipeline and fin in each unit As radiative heat rejection face.The fin arrangement of the radiator can with flexible design, can also be used multi-pipeline reinforce fluid and fin it Between heat exchange.Meanwhile that there is also fin temperature uniformities is poor, weight demands are high, runner design is complicated etc. lacks for this radiator It falls into.

With the rapid development of space technology in recent years, the functional requirement of spacecraft is continuously improved, satellite equipment equipment Highly integrated, high power density single machine heat consumption gradually increases.And above-mentioned several existing space radiators can not expire well The thermal control requirement of high power density single machine on sufficient star.Therefore, there is an urgent need to a kind of radiating efficiency height, simple process, reliable now Property the high, radiator that occupies little space solve heat dissipation problem when high power density single machine is operated at full capacity for a long time on star.

Summary of the invention

It is an object of the present invention to overcome the above-mentioned drawbacks of the prior art and provide on the strong star of heat-sinking capability High power density single machine fluid circuit radiator.

In order to realize that the purpose of the present invention, the application provide following technical scheme.

In the first aspect, the application provides high power density single machine fluid circuit radiator on a kind of star, the radiation Device includes cellular board, fluid line, heat-sink unit and equal hot cell, and the cellular board is hollow structure, and the fluid line is solid Fixed to be arranged in cellular board, the heat-sink unit is fixed on the side of cellular board Environment Oriented, and is used for the heat of cellular board Pass to environment；The equal hot cell is fixed on side of the cellular board backwards to environment, and is used for the isothermal of cellular board.

In a kind of embodiment of first aspect, the fluid line disk-shaped distribution in cellular board.

In a kind of embodiment of first aspect, fin is arranged in the two sides of the fluid line.

In a kind of embodiment of first aspect, the heat-sink unit is the silver-plated second surface mirror of cerium glass.

In a kind of embodiment of first aspect, the heat-sink unit be fixed on by way of bonding cellular board towards The side of environment.

In a kind of embodiment of first aspect, the equal hot cell be samming heat pipe, and the samming heat pipe and stream Body pipeline monitor arrangement.

In a kind of embodiment of first aspect, the material of the cellular board is aluminium.

Compared with prior art, the beneficial effects of the present invention are:

(1) fluid line is integrated with aluminum honeycomb panel, reduce the occupied space and weight of radiator；

(2) high temperature fluid enters aluminum honeycomb panel by the fluid line being embedded in cellular board, and then fluid passes through thermally conductive Aluminum honeycomb panel is transferred heat to, the samming heat pipe for being arranged in aluminum honeycomb panel side is recycled to carry out isothermal to aluminum honeycomb panel, Finally realized to space heat loss through radiation to high-power on satellite using the silver-plated second surface mirror of cerium glass of aluminum honeycomb panel outer surface Efficient, the rapid cooling of density single machine.

Detailed description of the invention

Fig. 1 is the structural schematic diagram of radiator Environment Oriented of the present invention side；

Fig. 2 is structural schematic diagram of the radiator of the present invention backwards to environment side；

Fig. 3 is radiator side structure schematic diagram of the present invention.

In the accompanying drawings, 1 is aluminum honeycomb panel, and 2 be fluid line, and 21 be fluid line entrance, and 22 go out bayonet for fluid line, 3 be samming heat pipe, and 4 be the silver-plated second surface mirror of cerium glass, and 5 be fin.

Specific embodiment

Unless otherwise defined, the technical term or scientific term used in the present specification and claims is should be The ordinary meaning that personage in the technical field of the invention with general technical ability is understood.That enumerates herein is all from most Low value to the numerical value between peak, refer to when between minimum and peak differ two units more than when, minimum with most All numerical value obtained using a unit as increment between high level.

A specific embodiment of the invention is described below with reference to attached drawing, it should be pointed out that in these embodiments During specific descriptions, in order to carry out brief and concise description, this specification can not be to all spies of actual embodiment Sign makees description in detail.Without departing from the spirit and scope of the present invention, those skilled in the art can be to this hair Bright embodiment is modified and is replaced, and gained embodiment is also within protection scope of the present invention.

Traditional space radiator has the problems such as radiating efficiency is low, structure is complicated, occupied space is big in varying degrees.Root Mainly have according to this special fence-Boltzmann's law and radiation heat transfer relative theory, the approach for reinforcing space radiator heat-sinking capability: one It is increasing heat radiation area；Second is that improving radiator surface temperature uniformity；Third is that increasing surface emitting-absorptance.The first side Formula is obviously not suitable for for giving the satellite model of configuration layouts, and high power density single machine fluid returns on a kind of herein described star Path radiation device is to pass through design optimization enhanced rad exchange capability of heat under conditions of not changing satellite structure layout and mounting means Second and the third mode, realize quickly, efficiently to space environment radiate purpose, and then solve star on high power density list Captain's time expires heat dissipation problem when power consumption work.

In a specific embodiment, the application provides high power density single machine fluid circuit radiator on a kind of star, The radiator includes cellular board, fluid line, heat-sink unit and equal hot cell, and the cellular board is hollow structure, the stream Body pipeline is fixed in cellular board, and the heat-sink unit is fixed on the side of cellular board Environment Oriented, and is used for honeycomb The heat transfer of plate is to environment；The equal hot cell is fixed on side of the cellular board backwards to environment, and is used for the isothermal of cellular board Change.The course of work of the radiator is as follows: high temperature fluid is by the fluid line that is embedded in cellular board, into aluminum honeycomb panel Portion, then high temperature fluid transfers heat to cellular board by conduction, recycles the equal hot cell for being arranged in cellular board medial surface Isothermal is carried out to cellular board, is finally radiated using high emission-absorptance heat-sink unit that cellular board lateral surface is pasted to space Efficient, rapid cooling to high power density single machine on satellite are realized in heat dissipation.Since fluid circuit is integrated in cellular board, because This reduces the occupied space and weight of radiator.

In a specific embodiment, the fluid line disk-shaped distribution in cellular board, the setting strengthen stream The exchange capability of heat of body and radiator improves radiator surface temperature uniformity.

In a specific embodiment, fin is arranged in the two sides of the fluid line, which strengthens fluid and spoke The exchange capability of heat of emitter improves radiator surface temperature uniformity.

In a specific embodiment, the heat-sink unit is the silver-plated second surface mirror of cerium glass, cerium glass silver-plated two Subsurface mirror belongs to high emission-absorptance component, can quickly distribute the heat of cellular board to environment.

In a specific embodiment, the heat-sink unit is fixed on cellular board Environment Oriented by way of bonding Side.

In a specific embodiment, the equal hot cell is samming heat pipe, and the samming heat pipe and fluid line Arranged crosswise.Make heat pipe and fluid circuit in cross-distribution, compensate for the insufficient defect of cellular board horizontal heat-transfer capability, realizes spoke The isothermal on emitter surface.

In a specific embodiment, the material of the cellular board is aluminium.The material density is small, and heating conduction is strong, has Conducive to the lightweight of rapid cooling and satellite.

In conclusion the radiator has, heat-sinking capability is strong, occupy little space, simple process, have good stability, safety can By the advantages that.It can be widely used for solving navigation satellite, telecommunication satellite, high power density microsatellite, manned spaceship and space station Heat dissipation problem under the high power density single machine long-time full power operation state carried on equal spacecrafts.