JPS6160109A - Heat dissipation controller - Google Patents

Abstract

PURPOSE:To facilitate easy connection of a heat transmission system between the heat source side and the heat dissipation side in the universe and attain the automatic transmission of heat, by providing a heat receiving member of the heat dissipation side between the heat transmission members set opposite to the heat source side. CONSTITUTION:A fluid serving as a heat medium is circulated by the function of a pump P1. Then a heat source 13 is cooled down and the working fluid in a bellows containers 11 is heated up. Thus the steam pressure is gradually increased and the container 11 is expanded against a spring 33. When an attachment/detachment member 27 has a contact with a heat receiving member 27 by the expansion of the container 11, a substrate 25 and a secondary pipeline 21 are heated up. Then the heat is transmitted to a circulating fluid by the function of a pump P2. The heat is dissipated into the universe space through a heat sink 19. The flexible bellows containers 47 containing attachment/detachment members 45 are attached at both sides of a heat transmission member 41A. The axial core of the container 47 is approximately coincident with the axial core of a hinge 39. The member 45 of the container 47 is always set opposite to a heat receiving member 43A of a substrate 43 regardless of the developing angle of a heat dissipation panel 37 and a main body panel 35.

Description

[Detailed Description of the Invention] [Technical Field of the Invention] 1. The present invention relates to heat radiation control equipment, and more specifically, to control heat generated within a spacecraft, such as an artificial 1m star, into outer space. The present invention relates to a device for controlling heat radiation.

[Technical Background of the Invention 1 For example, heat generated within a space vehicle such as a satellite or a space base is generally released into outer space by radiation. In this way, when releasing heat into space, in the case of a spacecraft that generates a relatively small amount of heat, heat is directly released into space from the surface of the panel carrying the heat-generating device or the surface of the spacecraft. A configuration that does this is sufficient.

However, in a spacecraft that generates a large amount of heat, in order to improve heat radiation efficiency, it is necessary to provide a special heat radiation surface to transfer heat from the heat source to the heat radiation surface. As a heat transfer system for transferring heat from a heat source to a heat radiation surface, a circulation system using a fluid as a heat medium is generally used. This fluid circulation system may be in a single loop configuration. However, the heat dissipation surface is exposed to space and is easily damaged by collisions, so trowels that disperse danger may have large differences in temperature, such as freezing. From the viewpoint of prevention and heat transfer efficiency, it is desirable to use different types of fluids on the heat source side and the heat radiation side, so it is common to divide the fluid circulation system into a plurality of loop configurations.

As mentioned above, when the fluid circulation system is divided into multiple loop configurations, it is reliable to connect the heat transfer parts of each loop configuration by fastening them with bolts or the like. But U,
When assembling and maintaining in space, work efficiency is poor, so operations such as Pole 1 to tightening are difficult. ' Therefore, conventionally, a flexible part such as a diaphragm is provided at the connection part of one loop structure (), and this flexible part is pressed into contact with the connection part of the other loop structure by fluid pressure, etc. There is. This configuration has a problem in that a separate pressurizing device or the like is additionally required. In addition, since the heat transfer to the connection part is constant, the hot stones on the heat source side will deviate from the appropriate acoustic range due to the influence of fluctuations in the heat radiation side.
1!2 A bypass circuit etc. should be installed in the loop configuration of the fluid on the heat source side to avoid the possibility of There is a problem with whether it is necessary to control the

As mentioned above, a special heat dissipation surface is provided (J, S,
The heat dissipation area can be greatly increased and the h9 thermal capacity can be expanded. In order to avoid increasing the size of a satellite, for example in an artificial satellite, it is desirable to use a deployable heat dissipating surface that spreads out in space after hitting the ball. This J,
In the case where the heat dissipation surface is a deployable type, there is no suitable H formula to transfer heat from the heat source to the heat dissipation surface, and for example, the heat source and the heat dissipation surface are connected via a flexible vibrator. death,
It is also possible to have a configuration in which a fluid such as a heat medium is circulated within the pipe. However, in this case, pumps, etc. are required, and in addition to trying to increase the eaves of artificial satellites, etc.
There is a problem C.

[Objective of the Invention] The present invention was invented in view of the conventional problems such as d) and e. It is an object of the present invention to provide a heat radiation control device that can be easily connected to a transfer system and can automatically adjust heat transfer to a heat radiation side.

A second object of the present invention is to provide a heat radiation control device that can easily transfer heat from a heat source to a heat radiation surface even when the radiation surface is of an expandable type.

[Summary of the Invention] In order to achieve the above-mentioned object, the present invention arranges a heat receiving member on the heat radiation side between the heat transfer members facing the heat source side, or arranges a heat receiving member on the heat radiation side. Heat-receiving members provided oppositely□
A heat transfer member on the heat source side is arranged between the bases of a pair of expandable bellows containers filled with working fluid.
The bellows female container is attached to the heat transfer member, and the free end of each bellows female container is provided so as to be able to come into contact with and separate from the heat receiving member. To the heart [
:l-X The axis of the container is approximately aligned with the axis of the container.

[Embodiments of the Invention] =4- Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.

Referring to FIG. 1, the heat radiation control device 11. J, heat source side 3
a heat transfer section 5 provided on the heat radiation side 7, a heat receiving section 9 provided on the heat radiation side 7, etc.
The heat transfer section 5 is comprised of a telescopic container L"41 and a pair of bellows containers 11.

On the heat source side 3, there are five primary pipes 15 connected to the heat source 13 of the spacecraft.In this primary pipe 15, an appropriate fluid as a heat medium is circulated by a pump [1]. This primary pipe 15 is provided with a pre-heat distribution section 5 in stages.The heat transfer section 5 is, in this embodiment, a plate-shaped heat transfer member 17A.

A substantially ( )-shaped board 17 with 17B facing each other is provided. It is fixed. The heat dissipation side 7 consists of a secondary pipe 21 connected to a heat dissipation plate 19 of an appropriately configured structure, and an appropriate fluid is circulated within this secondary pipe 21 by a pump P2.
The heat receiving section 9 is provided in the next pipe 21 . In this embodiment, the heat receiving portion 9 is a plate-shaped heat receiving member 2 disposed between the opposing heat transfer members 17A and 17[3].
3 is integrally provided with a T-shaped K (plate 25 is installed (-
], and this substrate 25 is integrally attached to the secondary pipe 21 by appropriate fixing means.

- The bellows containers 11 of the moon are sealed with a suitable working fluid and are expanded by thermal expansion of the working fluid or increase in internal vapor pressure, and the base of each bellows container 11 is It is fixed to the heat transfer members 17Δ, 17B. At the free end of each bellows container 11, a plate-shaped connecting/separating member 27 is attached 4J, which can freely contact and detach from the heat receiving member 23. Brackets 1 to 29 are installed at an appropriate number of locations on this contact/separation member 27).
29 and heat transfer part + guide fixed to J17A, 17B [
] A suitable ammunition device 33 such as a coil spring is installed between the bellows container 11 and the bellows container 11 to constantly contract it.

Although detailed illustrations are omitted, the bellows container 1
1 has a heat transfer part (A17△, 17.13 to contact N1
Appropriate measures are taken to efficiently transfer heat to the shrine 27. That is, for example λ, the bellows container 11
The bellows container 11 may be configured in various ways, such as by having a plurality of heat plates in surface contact with each other and the contacting/separating member 27 in a movable manner, or by covering the inside of the bellows container 11 with a heat pipe. is possible.

In the above configuration, when the fluid as a heat medium is circulated between the heat source 13 and the primary pipe 15 due to the action of the pump P1, the heat of the heat source 13 is transferred to the fluid, and the heat source 13 is cooled. Become. The heat of the above fluid is transferred to the primary compartment 15
from the heat transfer member 17Δ of the substrate 17 in the heat transfer section 5,
One message was sent to 17B. Therefore, 11-space container 1
The fluid in the base container 11 is heated, and the steam pressure in the base container 11 gradually increases to 10'. 11 is extended against the bullet 1''3:33. In this case, Kla of the contact/separation member 27 provided at the free end of the base container 11 is It is determined by the condition that the vapor pressure in the 11-z container 11 and the horizontal force of the bullet Ijl! 33 are balanced.

Due to the extension of the bellows container 11, the contact/separation member 27 moves to the heat receiving part 9.
When it comes into contact with the heat receiving member 23 of
The heat is transferred to the substrates 25 and 2 of the heat receiving section 9.
Next, the pipe 21 is heated.

Therefore, due to the action of pump P2, heat sink 19.2
Heat is transferred to the fluid circulating in the piping 21, and the heat is radiated to outer space at the heat radiating plate 19.

When the above-described heat transfer is performed and the bellows container 11 is cooled by being radiated by the heat sink 19, the vapor pressure inside the bellows container 11 decreases, and the bellows container 11 is contracted by the action of the elastic machine 33. Therefore, contact/separation part 0
27 is separated from the heat receiving member 23 of the heat receiving part 9 +1t2 L,,
Transfer of heat from the heat source side 3 to the heat radiation side 7 is blocked. Therefore, the heat source side 3 will not be overcooled and will always be maintained within the optimum humidity range.

In this embodiment, the heat receiving member 23 provided on the heat radiation side 7 is positioned between the ends of the pair of bellows containers 110 provided on the heat source side 3.
, easier assembly and improved workability in space -1=
-v.

FIG. 2 shows a second embodiment. In this embodiment, the substrate 17 on the heat source side 3 is formed into a rectangular frame, and the primary pipes 15 are arranged on both sides of this WiN 17. be.

In the center of the substrate 17, a secondary pipe 21 is arranged in a direction perpendicular to the first arbitrary pipe 15.
1 has a rectangular heat receiving part + A23] [No C is included. At four locations on the inner surface of the substrate 17, a contact portion (A27 facing the heat receiving member 23)
is installed.

FIG. 3 shows the 0th embodiment, in which the bellows container 11 expands and contracts in a direction perpendicular to the longitudinal direction of the primary pipe 15, and the substrate 1 moves in the longitudinal direction of the primary pipe 15.
7 is shown. In this way, the board 1
By arranging a plurality of heat sources 7, it is possible to cope with cases where the heat generation ω of the heat source 13 is large.

FIG. 4b shows a fourth embodiment, and therefore shows a structure in which the base plate 17 is extended in the longitudinal direction of the primary pipe 15 in such a manner that the heavelows container 11 expands and contracts in the longitudinal direction of the primary pipe 15. There is.

FIG. 5 shows the heat radiation side 7 with respect to the main body panel 35 on the heat source side 3.
The heat dissipation panel 37 is pivotally attached via a hinge pin 39 so as to be expandable. In this embodiment, the heat transfer member 4.1 A of the substrate 41 is attached to the main body panel 35 and the Ij 11 plate 4 is attached to the heat dissipation panel 37.
The heat receiving members 43A of No. 3 are arranged alternately, and the heat transfer portion U
A telescopic bellows container 47 equipped with a jaw joint 45 is attached to both sides of the container 41A. The axis of the bellows container 47 substantially coincides with the axis of the hinge pin 39.

Therefore, in this embodiment, regardless of the unfolding angle of the heat radiation panel 37 with respect to the main body panel 35, the contact/separation member 45 of the bellows container 47 and the heat receiving member 43 of the substrate 43
He is always facing A. Therefore, heat dissipation panel 3
Even if the development of 7 is not sufficient, heat transfer from the main body panel 35 side to the panel 37 side '1M1l
l'i is actually done in 61r' 1! do.

Figures 6 and 7 show that both the main body panel 35 and the bold panel 37 have a honeycomb structure.
The heat transfer member 49 and the heat receiving member 5 equipped with the gas container 47
1 is an example in which 1 is a heat pipe. In this embodiment, a relay heat pipe 53 connected to a heat source as appropriate is connected to the main body panel 35 with 1iQI.
] Improving the heat transfer coefficient from the C1 heat source to the heat transfer part 4449
It's tight. Furthermore, the heat dissipation panel 37 is provided with a diffusion heat pipe 55 for spreading the heat from the heat receiving member 51 to improve heat dissipation efficiency. This embodiment also provides the same effects as the previously described embodiment.

FIGS. 8 and 9 show still another embodiment. In this embodiment, heat transfer members 49A and 'L9B made of heat pipes are provided on both the inner and outer sides of the main body panel 35.
, and pipes 53A and 53B to the relay heater 1 are also arranged in the main body panel 35 in duplicate. How to use: The heat receiving member 51, which is made of a heat pipe and installed on the heat dissipation panel 37, is bent into a substantially U-shape.
The axis of the portion facing between the heat transfer members 49A and 1I9B coincides with the axis of the hinge pin 39. The portion where the contact/separation member 45 of the bellows container 47 attached to the heat transfer members 49A, 49B contacts the heat receiving member 51 is formed into a shape corresponding to the outer shape of the heat receiving member 51 (in this embodiment, an arc shape). It is.

This embodiment also achieves the same effects as the previously described embodiment.

[Effects of the Invention] As can be understood from the description of the embodiments above, the present invention allows easy connection between the heat transfer system on the heat source side and the heat transfer system on the heat radiation side. At the same time, the heat transfer from the heat source side to the heat radiation side can be automatically adjusted. Further, even in a configuration in which the heat radiation side is expandably connected to the heat source side, heat can be easily transferred from the heat source side to the heat radiation side.

[Brief explanation of drawings]

The drawings show embodiments of the present invention, so FIG. 1 shows the first embodiment of the heat radiation control device, FIG. 2 is a front view of the second embodiment, and FIGS. Each figure is a perspective view showing an embodiment of the present invention, Fig. 5 is a t iF side view showing the case where the heat source side and the heat radiation side are connected in a freely deployable manner, and Fig. 6 is a front view of another embodiment. , FIG. 7 is a sectional view taken along the VU-■ line shown in FIG. 6, FIG. 8 is a front view of another embodiment, and FIG. - It is a cross-sectional view taken by IX-ray.

Claims (2)

[Claims] (1) A heat receiving member on the heat radiation side is arranged between heat transfer members provided facing the heat source side, or a heat transfer member on the heat source side is arranged between heat receiving members provided facing the heat radiation side. a pair of expandable and retractable bellows containers filled with a working fluid, the bases of which are attached to the heat transfer member, and the free end of each bellows container is provided so as to be freely movable toward and away from the heat receiving member; A heat radiation control device featuring: (2) The heat source side and the heat radiation side are rotatably connected via a hinge pin, and the axis of the hinge pin and the axis of the bellows container are substantially aligned. The heat radiation control device according to item 1.