KR200408043Y1 - A multiplex heat pipe - Google Patents

Abstract

The multi-heat pipe 100 according to the present invention is configured by connecting the tubing 111 of the plurality of heat pipes 110 in parallel and integrally, and thus, can reduce the weight of the satellite body and reduce the heat transfer efficiency due to the thermal contact resistance. It relates to a multi-heat pipe 100 that can be prevented.

Satellite, heating panel, heat pipe, multiple heat pipe, wick, groove

Description

Multiple Heat Pipes {A multiplex heat pipe}

1 is a cross-sectional view showing a longitudinal cut of the heat pipe to which the prior art is applied.

FIG. 2 is a cross-sectional view taken along the line AA ′ of FIG. 1.

3 is a front view illustrating a state in which a plurality of heat pipes to which a conventional technique is applied are attached to a heating panel;

4 is a cross-sectional view taken along the line CC ′ of FIG. 3.

FIG. 5 is a perspective view showing a local incision showing that a heat pipe to which a conventional technique is applied is embedded in a panel. FIG.

Figure 6 is an enlarged cross-sectional view showing the mutual contact surface of the heat pipe to which the prior art is applied.

7 is a partial cross-sectional view showing a cut-out of a multi-heat pipe to which the technique of the present invention is applied in a longitudinal direction, and showing that the fill tube is welded at both ends.

FIG. 8 is a cross-sectional view of a multi-heat pipe to which the technique of the present invention is applied in a longitudinal direction, and shows a sectional view showing that the fill tube is welded to the tubing side.

9 is a cross-sectional view taken along line B-B 'of FIG. 7 as to a multi-heat pipe to which the technique of the present invention is applied.

10 is a perspective view of a local incision showing the built-in panel for a multi-heat pipe to which the technique of the present invention is applied.

* Description of the symbols used in the main parts of the drawings *

110: heat pipe

111: tubing

113: capillary structure

115: end cap

117: fill tube

135: panel

The present invention relates to a multi-heat pipe, more specifically, by forming a plurality of heat pipes integrally in multiple, it is possible to reduce the weight of satellites such as satellites, and to prevent the heat contact resistance to multi-heat pipe with excellent heat transfer efficiency It is about.

1 is a cross-sectional view showing a conventional heat pipe cut in the longitudinal direction, Figure 2 is a cross-sectional view taken along the line AA 'of Figure 1, Figure 3 is a plurality of heat pipes to which the prior art is applied 4 is a cross-sectional view taken along line C-C 'of FIG. 3, and FIG. 5 is a local incision showing that a heat pipe to which a conventional technique is applied is embedded in the panel. 6 is an enlarged cross-sectional view showing mutual contact surfaces of heat pipes to which the prior art is applied.

In general, the heat pipe 10 is used in aerospace-related fields such as satellites, and is used to prevent overheating by performing heat transfer.

The heat pipe 10 is welded to the end cap 15 and the opposite end of the end cap 15 which are welded to seal the tubing 11 and one end of the tubing 11 in a tubular shape, and a working fluid. Is composed of a fill tube (17) and the working fluid is injected into the tubing (11) through the fill tube (17), the inner surface of the tubing (11) so that the working fluid becomes a liquid It consists of a capillary structure 13 formed of a wick (porous structure that can serve as a wick) or groove.

Looking at the use example of the heat pipe 10, as shown in Figure 3 using a plurality of brackets 20, a plurality of heat pipes 10 are used to be attached to the heating panel 30 in contact with each other, or as shown in FIG. A panel 35 having a plurality of heat pipes 10 in contact with each other by the bracket 25 is attached to the heating panel 30 and used.

Looking at the operation example of the heat pipe 10 mounted on the heat generating panel 30, when heat is generated in the heat generating panel 30, the working fluid filled in the heat pipe 10 in contact with the heat generating unit is a gas After absorbing the latent heat, and moves along the inside of the tubing 11 to dissipate heat from the cooling unit, the cycle of returning to the heating unit through the capillary structure 13 to the liquid is repeated to heat the heat of the heating unit to the cooling unit It serves as a heat pump to deliver.

In the case of the heat pipe 10 according to the above-described configuration and operation, the size of the heat pipe 10 must be increased or the mounting quantity must be increased in order to increase the amount of heat transfer. In the case of increasing the size, the panel 35 containing the heat pipe 10 is embedded. ), There is a problem that the weight of the satellite body increases due to the increase in size, and when the mounting quantity is increased to form the panel 35 densely, it is not necessary to increase the size of the panel 35, but a plurality of heat pipes 10 By using a plurality of brackets (25) to keep in contact with each other) will also lead to an increase in weight.

In addition, when a plurality of heat pipes 10 are used in contact with each other, the heat transfer efficiency is low due to the thermal contact resistance.

The thermal contact resistance is the contact of each heat pipe 10 as shown in FIG. The contact surface M is contacted only through a very limited number of contact points P, so that heat conduction occurs through the contact point P and conduction or convection through the fluid layer of the space W formed between the contact surfaces M. Is generated, and heat is transferred by radiation between the surfaces facing each other, which means a thermal resistance induced. Therefore, a detailed description thereof is omitted since it is known to those skilled in the art.

In order to solve the above problems, in the present invention, a plurality of heat pipes are integrally formed to be improved by multiple heat pipes, so that the heat pipes can be mounted on the heating panel without using a bracket for contacting the heat pipes, and the panel is compact. It can be easily accommodated to reduce the weight of the satellite, and the object of the thermal contact resistance is prevented to provide a multi-heat pipe with excellent heat transfer efficiency.

Hereinafter, with reference to the accompanying drawings, look at the configuration and effect of the present invention for achieving the above object.

FIG. 7 is a cross-sectional view showing a cut tube welded at both ends of the multi-heat pipe to which the technique of the present invention is applied, and FIG. 8 is a longitudinal view of the multi-heat pipe to which the technique of the present invention is applied. Fig. 9 is a cross-sectional view taken along the line B-B 'of Fig. 7 as a cutaway view showing a fill tube welded to both sides as shown in FIG. The present invention relates to a multi-heat pipe to which the technique of the present invention is applied, which will be described together as a local cutaway perspective view showing a built in panel.

In general, the heat pipe 110 is used in aerospace-related fields such as satellites, and is used to prevent overheating by performing heat transfer.

The heat pipe 110 is welded to the end cap 115 and the opposite end of the end cap 115 welded to seal the tubing (111, tubing) of the tubular shape and one end of the tubing 111 and the working fluid Is composed of a fill tube 117 and the working fluid is injected into the tubing 111 through the fill tube 117, the working fluid becomes a liquid on the inner surface of the tubing 111 It consists of a capillary structure 113 formed of a wick (porous structure that can serve as a wick) or groove.

In the present invention, the tubing 111 of the plurality of heat pipes 110 are integrally connected in parallel, and the fill tube 117 is formed at the end of the tubing 111 as shown in FIG. 7, or as shown in FIG. 8. The structure formed in the side surface S of the tubing 111 is possible.

According to the above configuration, a bracket for contacting and attaching a plurality of heat pipes 110 is unnecessary. That is, in the case of the heat pipe 110 formed of a single, it should be made a solid contact with a plurality of brackets in order to reduce the thermal contact resistance, but in the present invention, since each tubing 111 is formed integrally, each heat pipe The bracket for contacting and fixing 110 may be omitted.

Therefore, when attached to the heating panel or used in the panel 135, the bracket can be omitted, thereby reducing the weight of satellites such as satellites.

Of course, when attaching to the heating panel, a few brackets for attaching to the heating panel is of course used.

In addition, since each tubing 111 is integrally formed, all the heat is transferred by conduction, so that a decrease in the heat transfer efficiency due to the thermal contact resistance can be prevented, thereby enabling rapid heat transfer.

According to the present invention by the above configuration, by forming each of the tubing integrally to configure the heat pipe in multiple, it is possible to reduce the weight of the satellite body, it is possible to prevent the degradation of heat transfer efficiency due to thermal contact resistance aerospace There is an effect that can contribute to industrial development.

Claims (1)

In the conventional heat pipe 110 composed of tubing 111 of the tubular shape, Multiple heat pipes, characterized in that the plurality of heat pipes 110 is configured in which the tubing 111 is integrally connected in parallel.

Images