CN102079386A

CN102079386A - Simply constructed heat transfer device for stand-alone radiating of space vehicle

Info

Publication number: CN102079386A
Application number: CN2009101996818A
Authority: CN
Inventors: 姚正平; 于迎军; 胡明亮
Original assignee: Shanghai Institute of Satellite Engineering
Current assignee: Shanghai Institute of Satellite Engineering
Priority date: 2009-11-30
Filing date: 2009-11-30
Publication date: 2011-06-01

Abstract

The invention discloses a simply constructed heat transfer device for stand-alone radiating of a space vehicle, which comprises an outer stuck heat pipe [5], a heat end heat-expansion plate [3], a cold end heat-expansion plate [7], a radiator [8], a heat end cover plate [2] and a cold end cover plate [6], wherein the outer stuck heat pipe [5] transmits the heat of the stand-alone [1] to the radiator [8]; the heat end cover plate [2] and the cold end cover plate [6] are used for fixing the outer stuck heat pipe [5]; and the heat end heat-expansion plate [3] and the cold end heat-expansion plate [7] are used for enhancing the heat transfer effect of the outer stuck heat pipe [5]. According to the invention, the problem of radiating an efficient heat transfer channel of the stand-alone of the space vehicle is solved, and the beneficial effects such as low cost, high reliability, good heat transfer effect and the like, are achieved.

Description

A kind of simple and easy heat transfer apparatus of space vehicle unit heat-dissipation that is used for

Technical field

The present invention relates to the simple and easy heat transfer apparatus of space vehicle unit heat-dissipation.

Background technology

In the space vehicle thermal control system, usually need some instrument and equipment or parts are taked insulation or cooling measure, regulate the unit temperature as far as possible in the temperature index scope that is fit to its work.For unit in most of star, can guarantee its heat radiation requirement by the mode of opening heat delivery surface at the unit adapter plate.But for the special unit of part, as satellite gyro, driver train etc., the unit setting accuracy requires high, and power consumption is big, and temperature index requires high.And in order to satisfy its requirement on electric performance, unit heat radiation requirement often can not be taken into account in its installation site.Can not satisfy its heat radiation requirement by the mode of opening heat delivery surface at the unit adapter plate this moment, and seeking new heat transfer channel is to solve unit heat-dissipation the only resource.

At present, being used for space vehicle heat-dissipation heat transfer apparatus has:

1, quarter-phase circuit heat transfer apparatus, this device is made up of evaporator, steam pipe, condenser, fluid pipeline and reservoir based on the groundwork of capillary pumped two-phase fluid heat transfer loop.Liquid refrigerant flows out evaporator in the heat absorption evaporation of the surface of capillary wick through evaporator in-to-in steam channel, enters steam pipe, enter condenser condenses then and be liquid and must be cold, release heat.Under the effect of capillary force, flow back to evaporator through fluid pipeline again.In the heat transfer apparatus of whole loop, the wick structure in the evaporator can provide necessary mobile propulsive effort, and does not need to consume any external force acting.The major defect of this device is that Heavy Weight, system complex, reliability are low, is used for the heat radiation of local unit, and cost is too big.

2, phase-change accumulation energy device, the principle of work of this device is, the phase-change material that latent heat is bigger is placed between controlled device and the external environment, when the interface temperature of phase-change material and heat element is elevated to the fusing point of phase-change material, the phase-change material fusing, absorb heat by the latent heat of fusion, interface temperature is still remained near the melting point.Because inner or exterior former thereby when descending, phase-change material is emitted latent heat and is solidified when the temperature at interface.The phase-change accumulation energy device is mainly used in the superpower unit of instantaneous work, is not suitable for the unit heat radiation of long-term stable operation.

Summary of the invention

In order to solve above-mentioned prior art systems complexity, to take deficiencies such as aggregate resource is many, the object of the present invention is to provide a kind of simple and easy heat transfer apparatus of space vehicle unit heat-dissipation that is used for.Utilize the present invention, not only reached the heat radiation requirement of unit, and package unit is simple and easy reliable, cost is low.

In order to reach the foregoing invention purpose, the technical scheme that the present invention is adopted for its technical matters of solution provides a kind of simple and easy heat transfer apparatus of space vehicle unit heat-dissipation that is used for, and this device comprises: paste heat pipe outward, expand hot plate and cover plate etc.

During unit work, heat is transferred to exciter by expanding hot plate and pasting heat pipe outward, because exciter outside face spraying high efficiency and heat radiation coating, heat is diffusing again to cold space by exciter.

The present invention is a kind of simple and easy heat transfer apparatus of space vehicle unit heat-dissipation that is used for, owing to take outer subsides adopting heat pipes for heat transfer, expansion hot plate to strengthen the mode of hot laser propagation effect, therefore, has reached following beneficial effect:

1. install simple and easyly, cost is low, and package unit only needs common curved hot pipe and expand hot plate just to reach heat-transfer effect, compares much simple with the quarter-phase circuit heat transfer apparatus of being made up of parts such as evaporator, condensers;

2. reliability height does not exist startup, termination and the Problem of Failure of system, and the diplopore heat pipe has improved the reliability of system;

3. heat-transfer effect is good, and paste heat pipe outward and expand the hot plate combination, the heat transfer potential foot, the unit heat can effectively be transferred to exciter, and looses to cold space.

Description of drawings

Fig. 1 is a kind of structural representation that is used for the simple and easy heat transfer apparatus of space vehicle unit heat-dissipation of the present invention, and wherein Figure 1B is that the A of Figure 1A is to view;

Among the figure: hot plate, 4 unit adapter plates, 5 outer heat pipe, 6 cold junction cover plates, 7 cold junctions expansion hot plate, 8 exciters of pasting are expanded in 1 unit, 2 hot junction cover plates, 3 hot junctions;

Fig. 2 is the outer structural representation that pastes heat pipe; Wherein: Fig. 2 B is the section-drawing of Fig. 2 A.

The specific embodiment

Below in conjunction with description of drawings the preferred embodiments of the present invention.

Fig. 1 is a kind of structural representation that is used for the simple and easy heat transfer apparatus of space vehicle unit heat-dissipation of the present invention, and Figure 1B is that the A of Figure 1A is to view; This device comprises:

The hot junction is expanded between hot plate 3 and the unit adapter plate 4, contact area scribbles heat-conducting silicone grease between cold junction expansion hot plate 7 and the exciter 8, hot plate 3 is expanded in the hot junction, cold junction expands hot plate 7 the outer fluting road, zone that pastes heat pipe 5 is installed, and by hot junction cover plate 2 and the cold junction cover plate 6 fixing outer heat pipes 5 that paste; Outer paste that heat pipe 5 expands hot plate 3 with the hot junction, cold junction expands hot plate 7 contact areas and is filled with heat filling, heat filling is the thick indium foil of 0.017mm, is coated with behind the vacuum silicone grease pad and is contained in the hot junction and expands hot plate 3, cold junction and expand between hot plate 7 and the outer subsides heat pipe 5.Exciter [8] outside face spraying high efficiency and heat radiation coating, the coating infrared emittance is higher than 0.85, and solar absorptance is lower than 0.18.

Fig. 2 is the outer structural representation that pastes heat pipe; Wherein: Fig. 2 B is the section-drawing of Fig. 2 A.As shown in Figure 2, pasting heat pipe 5 outward is the aluminium conduit ammonia working medium diplopore heat pipe that two external diameters are 7mm, and its heat transfer capability is not less than 80wm, and the long-term power consumption of unit 1 shown in Figure 1 is not more than 40W, satisfies unit heat radiation requirement.The outer heat pipe two ends of pasting are fixed by cover plate, and unsettled place coats a circle with the wool felt that 2mm is thick, 10mm is wide, and fix with polyimide single face pressure sensitive adhesive.

To shown in Figure 2, unit 1 expands hot plate 3, pastes heat pipe 5 and cold junction outward and expand hot plate 7 heat is transferred to exciter by the hot junction as Fig. 1, and the high efficiency and heat radiation coating of exciter outside face guarantees that heat looses to cold space.Package unit is simple and easy reliable, and actv. has satisfied the heat radiation requirement of unit 1.

Claims

1. one kind is used for the simple and easy heat transfer apparatus of space vehicle unit heat-dissipation, it is characterized in that, unit [1] is transferred to exciter by the outer heat pipe [5] that pastes with heat, increase the hot junction between unit [1] and the unit adapter plate [4] and expand hot plate [3] reinforcement heat conduction, exciter [8] expands hot plate [7] by cold junction and adds the heat-flash laser propagation effect, pastes heat pipe [5] two ends outward and fixes by hot junction cover plate [2] and cold junction cover plate [6].This device also comprises: paste the unsettled place of heat pipe [5] outward and coat with wool felt; The hot junction is expanded hot plate [3] and is scribbled heat-conducting silicone grease with unit adapter plate [4], cold junction expansion hot plate [7] with exciter [8] contact area; The outer heat pipe [5] that pastes expands hot plate [7] contact area and is filled with heat filling with hot junction expansion hot plate [3], cold junction; Hot junction cover plate [2] expands hot plate [3] with the hot junction, cold junction cover plate [6] is fixing in succession by screw with cold junction expansion hot plate [7].

2. the simple and easy heat transfer apparatus of space vehicle unit heat-dissipation that is used for according to claim 1 is characterized in that: described outer subsides heat pipes [5] are aluminium conduit ammonia working medium diplopore heat pipe.

3. the simple and easy heat transfer apparatus of space vehicle unit heat-dissipation that is used for according to claim 1 is characterized in that: described exciter [8] outside face spraying high efficiency and heat radiation coating.

4. the simple and easy heat transfer apparatus of space vehicle unit heat-dissipation that is used for according to claim 1, it is characterized in that: hot plate [3] is expanded in described hot junction, cold junction expands hot plate [7] all black anodizing processing except that mounting hole and attachment face, expand hot plate thickness greater than the outer external diameter that pastes heat pipe [5], guarantee the outer installing space that pastes heat pipe [5].