JPS60117090A - Heat dissipation control device - Google Patents

Abstract

PURPOSE:To obtain a heat dissipation control device with high reliability such as an apparatus loaded in artificial satellite or the like by a structure wherein elastic spheres containing fluid heat transfer medium therein and interposed between an expansion container and a radiator plate. CONSTITUTION:Heat transfer medium 11 is a fluid made of single phase substance, which is excellent in heat conduction. In addition, three kinds of shape memory alloys 8, 9 and 10 have higher working temperatures in the order named. The heat transfer medium 11 excellent in heat conduction is encapsulated in elastic spheres 12. When an apparatus loaded develops heat and the temperature of a panel 2 rises, the temperature in an expansion container 14 also rises. When said temperature in the container 14 reaches the specified value, at first, a shape memory alloy spring 8 extends so as to press a contactor plate 5 against the elastic spheres 12. The heat in the expansion container 14 is transmitted in the order of the contactor plate 5, the elastic spheres 12 and a radiator plate 6 in order to be dissipated in cosmic space. In proportion to the further increase of the calofic value of the apparatus 1, the shape memory alloys 9 and 10 extend in the order named, resulting in making the elastic spheres 12 flatter and flatter and consequently the heat quantity to be conducted to the radiator plate 6 more and more. Thus, the quantity of heat dissipation increases in proportion to the calorific value of the apparatus 1, resulting in keeping the temperature in the apparatus 1 at the specified value.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Application of the Invention] The present invention relates to a heat radiation control device, and particularly to a heat radiation control device suitable for use in space industrial equipment such as artificial satellites.

[Background of the invention]

The space industry is a growing industry in the future, and establishing heat control technology in the space environment, especially heat radiation control technology for equipment onboard satellites, has become an important issue.

First, a conventional heat radiation control device will be explained with reference to FIGS. 1 and 2.

FIG. 1 is a schematic cross-sectional view of a conventional heat radiation control device, and FIG. 2 is a warping operation characteristic diagram.

In FIG. 1, numeral 1 indicates onboard equipment such as equipment onboard an artificial satellite, and numeral 2 indicates a channel provided at the bottom of the onboard equipment 1.

3 is a working medium whose pressure changes depending on the temperature; 4 is a compression container; it is composed of an elastic body 4a such as a bellows and a contact/separation plate 5;
It is attached to the panel 2 and contains the working medium 3. A heat sink 6 is provided at the end of the expandable container 4.

When the amount of heat generated by the mounted equipment 1 increases, the temperature of the working medium 3 increases, and therefore the internal pressure of the expandable container 4 increases. Therefore, the expandable container 4 is stretched, and when the temperature inside the container reaches a certain level or higher, the contact/separation plate 5 is pressed against the heat sink 6. Therefore, the amount of heat radiation shown by the thick white arrow 7 increases, and the temperature inside the expandable container 4 and the temperature of the mounted equipment 1 are maintained at a constant temperature within a certain range of calorific value.

Figure 2 shows the temperature change of the onboard equipment 1. Here, Q on the horizontal axis
is the heat generated by the onboard equipment, and T on the vertical axis is the temperature.

Such conventional heat radiation control devices have the following problems.

(1) A refrigerant or the like is used as the working medium 3, and the heat transfer coefficient generally varies depending on temperature, pressure, and degree of freshness. In other words, the thermal resistance inside the expandable container 4 varies depending on the state, so controllability is poor.

(2) The contact/separation plate 5 and the heat dissipation plate 6 are in contact with each other by pressing and pressing flat plates made of an appropriate material. In this case, the contact thermal resistance is greatly influenced by the surface roughness, dirt, etc. of both flat plates. How many times is it in contact?

As the previous discussion is repeated, the surface properties mentioned above will change, and there is a concern that the value of the contact thermal resistance will change accordingly. Furthermore, in the example of the device shown in FIG.
If small particles were to get caught between the two flat plates, the contact thermal resistance would immediately increase significantly, potentially drastically reducing the heat dissipation effect.

[Object 1 of the Invention] The present invention has been made to solve the problems of the prior art described above, and has good heat dissipation controllability and reliability for controlling the internal temperature of equipment on board an artificial satellite. The purpose is to provide a high heat radiation control device.

[Summary of the invention]

The configuration of the heat radiation control device according to the present invention includes a fluid heat medium with excellent heat conduction and a plurality of shape memory alloy elastic members that operate at different temperatures of the heat medium, and the memory alloy elastic members operate. The method includes an expandable container that expands and contracts at a temperature of 100 degrees, and a heat sink, and one or more expandable bodies containing a fluid heat medium with excellent thermal conductivity are interposed between the expandable container and the heat sink. This is what I did.

[Embodiments of the invention]

Hereinafter, one embodiment of the present invention will be described with reference to FIGS. 3 to 5.

Figure 3 is a schematic cross-sectional view p1 of a heat radiation control device according to an embodiment of the present invention, Figure 4 is a schematic cross-sectional view showing the operating status of the device in Figure 3, and Figure 5 is its operation. It is a characteristic diagram. In the figure,
The same numbers as in FIG. 1 indicate parts equivalent to the conventional technique 1ti.

In Fig. 3, 14 is a telescopic container, and a telescopic body 1 such as a bellows.
4ζλ and a contact/separation plate 5, which are marked on the panel 2 of the on-board equipment 1. 11 is a fluid heat medium with excellent heat conduction. 8, 9, and 10 are springs related to elastic members made of three types of shape memory alloys, and the heat medium 11 in the expansion/contraction volume s: + 14
They are mounted in parallel inside.

The heat medium 11 is a single-phase fluid whose thermal conductivity does not change significantly depending on the pressure and temperature inside the container. Additionally, the three types of shape memory alloys are types that elongate when a specific temperature is reached, and each has a different operating temperature. In this example, 8, 9. The operating temperature increases in the order of j' and o. .

Reference numeral 12 denotes an elastic body, which contains a heat medium 11 with excellent thermal conductivity inside the spherical body of an elastic container made of rubber or plastic material. A plurality of heat dissipating plates 6 are interposed between the heat dissipating plate 6 and the heat dissipating plate 6 located at the bottom. The elastic body 12 is deformed into an inner shape by pressure when the adhesive plate 5 is pressed, increasing the heat transfer area from the contact/separation plate 5 to the heat dissipation plate 6.

The operation of such a heat radiation control device will be explained.

Heat radiation control devices are used for a variety of purposes, but are primarily needed in artificial satellites moving in outer space. In such applications, the outside of the heat sink 6 shown in FIG. 3 is exposed to outer space, and heat radiation 7 is performed by radiation. Now, when the mounted equipment 1 generates heat and the temperature of the panel 2 rises, the temperature inside the expandable container 14 also rises due to heat conduction through the heat medium 11. Expandable container 1
When the inside of 4 reaches a specific temperature, first, the shape memory alloy spring 8 stretches and presses the 2 contact and separation plates 5. At this time, the contact/separation plate 5 presses the expandable body 12, so that the expandable body 4a expands and the stretchable body 12 is deformed into an elliptical shape between the contact/separation plate 5 and the heat dissipation plate 6 and fixed. The heat inside the expandable container 14 is transferred to the separation plate 4. It is transmitted in this order to the extensible ball 12 and the heat sink 6, and is radiated into outer space as shown by the thick self-arrow 7. When the amount of heat generated by the mounted equipment 1 increases, the temperature inside the expandable container 14 further increases, and the shape memory alloy spring 9 expands. At this time, the elastic wire 12 is further pushed out and deformed into a flat shape, and the contact/separation plate 5 and the heat dissipation plate 6
Since the heat transfer contact area increases, the amount of conducted heat increases to 11η(
1. The amount of heat dissipation increases. Figure 4 shows this situation. When the amount of heat generated by the mounted equipment 1 is large, the shape memory alloy spring 10 expands due to the same action, and the expansion line 1
2 becomes even flatter and conductive heat increases.

The heat radiation control according to this embodiment will be explained below.
In the iA calendar, the amount of heat dissipated increases according to the onboard It$ and the heat generation base of the vessel J, and the temperature inside the onboard base 1 can be maintained at a specific value. FIG. 5 is a graph of this pattern as an operating characteristic diagram.

In Figure 5, Q on the horizontal axis is the amount of heat generated by the onboard equipment l, and T on the vertical axis is the temperature.Compared to the operating characteristics of the conventional heat radiation control device shown in Figure 2, the control range is long and stable. It is clear that there are

The heat radiation control device of this embodiment has the following major advantages over conventional heat radiation control devices.

(1) Since the inside of the expandable container 14 is a single-phase object made of a material with known thermal conductivity, fluctuations are small and controllability is good.

(2) The springs 3, 9, and 10 made of shape memory alloy are used, and their operation is reliable.

(3) Heat dissipation is carried out using a clear mechanism of changing the contact area of the elastic wire 12.
The heat radiation control device has good stability regardless of changes in surface conditions.

(4) Separation plate 5. Even if sand or dirt adheres to the surface of the heat sink 6, the controllability is not significantly affected and the reliability of the heat dissipation control device is high.

Next, another embodiment of the present invention will be described with reference to FIG.

FIG. 6 is a schematic cross-sectional view of a heat radiation control device according to another embodiment of the present invention. In the figure, the same parts and symbols as those in FIG. 3 are the same parts as in the previous embodiment, so the explanation thereof will be omitted.

In FIG. 6, reference numeral 15 denotes a telescoping container, which is composed of a telescoping body 15a and a detachable plate 5, and is attached to the panel 2 of the mounted equipment 1. =J
't has been blocked. Reference numerals 16 and 17 indicate springs made of two types of elastic members made of shape memory alloys, which are installed in series in the heat medium 11 in the expandable container 15, with the shape memory alloys having higher operating temperatures in the order of 16.17. It is used.

The operation of such a heat radiation control device will be explained.

When the Gake IJi device 1 generates heat and the temperature of the panel 2 rises, the temperature inside the expandable container 15 also rises due to heat conduction via the heat medium 11. When the inside of the expandable container 15 reaches a certain level, the shape memory alloy spring 16 first moves out and pushes the contact/separation plate 5 via the shape memory alloy spring 17, and the expandable body 15
a is expanded, and the elastic wire 12 is deformed into an ellipse between the tangent m1 and the heat sink 6 and fixed. The heat inside the expandable container 15 is transmitted in the order of the contact/detachment@5, the expandable ERJ2, and the heat sink 6, and is radiated into outer space in the direction of the thick white arrow 7. When the amount of heat generated by the mounted equipment 1 increases, the temperature inside the expandable container 15 further increases, and the shape memory alloy spring 17 expands. Therefore, due to the superimposed stretching force of the shape memory alloy springs 16 and 17, the elastic wire 12 is further pressed and deformed into a flat shape, and the contact area between the separation plate 5 and the heat sink plate 6 increases, so the amount of heat conducted increases and is dissipated. The amount of heat increases. Figure 6 shows this situation.

In this way, also in the case of a heat radiation control device in which the shape memory alloy springs 16 and 17 are installed in the expandable container 15 in series,
The same effect as in the case of the heat radiation control device in which the shape memory alloy springs 8, 9, and 10 shown in FIG. 3 are mounted in parallel in the expandable container 14 can be achieved.

In addition, in the above embodiment, two shape memory alloy springs were installed in series (Fig. 6) and three in parallel (Fig. 3), but the number should be designed according to necessity. Even devices with a combination of parallel and series structures are expected to have corresponding effects.

In addition, although the above-mentioned embodiment describes an example of a heat radiation control device provided for equipment onboard an artificial satellite, the present invention is not limited to equipment onboard an artificial satellite, and is expected to have similar effects. It is a general-purpose device in the range of heat radiation control devices.

〔Effect of the invention〕

As described above, according to the present invention, heat dissipation controllability for controlling the internal temperature of equipment onboard an artificial satellite, etc. is good, and li
tHighly reliable heat radiation control device i! can be provided.

[Brief explanation of the drawing]

1 is a schematic cross-sectional view of a conventional heat radiation control device, FIG. 2 is a diagram of its operating characteristics, FIG. 3 is a schematic cross-sectional view of a heat radiation control device according to an embodiment of the present invention, and FIG. 3 is a schematic cross-sectional view showing the operating status of the device shown in FIG. 3, FIG. 5 is a diagram showing its operating characteristics, and FIG. 6 is a schematic cross-sectional view of a heat radiation control device according to another embodiment of the present invention. It is. ■...ig a equipment, 2... Panel, 5... Separation plate, 6... Heat sink, 8, 9. ．． 10.16.17...
・Shape memory alloy agent Patent attorney Akiya Takahashi 1 Tomoe pole 2 n □ Q pole 4 eyes 11 ÷ Q Kakutsumura

Claims (1)

[Claims] ■ Contains a fluid heat medium with excellent thermal conductivity and a plurality of shape memory alloy elastic members that operate at different temperatures of the heat medium, and expands and contracts by the operation of the memory alloy elastic members. A retractable container and a heat radiating plate are provided, and one or more retractable balls containing a fluid heat medium with excellent thermal conductivity are interposed between the retractable container and the heat radiating plate. A heat radiation control device featuring: 2. The heat radiation control device according to claim 1, wherein a plurality of elastic members made of shape memory alloy are mounted in parallel in an expandable container. 3. The heat radiation control device according to claim 1, wherein a plurality of elastic members made of shape memory alloy are mounted in series within an expandable container.