JPH01249599A - Radiation cooling device - Google Patents

Abstract

PURPOSE:To perform an efficient control of temperature by transporting heat, transmitted to the first cooling unit, to the first opening part through the first heat pipe and heat, transmitted to the second cooling unit, to the second and first opening parts through the second and third heat pipes to be radiated. CONSTITUTION:Heat from a space navigating vehicle 30 is transported to the first opening part 10a through the first cooling unit 11, first heat pipe 13 and a heat radiator 14 and radiated. Simultaneously, heat from an infrared rays detector 19 is transported to the first and second opening parts 10a, 10b through the second cooling unit 17, second heat pipe 20, connection part 22, third heat pipe 23 and heat radiators 21, 24 and emitted. Here a beam of heat from the sun 31 is intercepted by an outside heat reflector 10. In this way, the infrared rays detector 19 is held to a desired temperature region. Thus because the outside heat reflector 10 separately provides the first and second opening parts 10a, 10b corresponding to different cool space, an efficient control of temperature can be performed by enabling the cool space of wide range to be ensured.

Description

[Detailed Description of the Invention] [Objective of the Invention] (Industrial Application Field) This invention is for example mounted on a space vehicle such as an artificial satellite, and used to detect infrared rays from an observed object such as the earth from outer space. The present invention relates to a radiation cooling device used to cool objects to be cooled such as infrared detectors.

(Prior art) In general, this type of infrared detector is
When detecting infrared rays from an I-body, the detector body is heated to a temperature of 80 to 12, which is very low compared to the inside temperature of the spacecraft.
It is required to cool down to a temperature range of around 0 and maintain it. For this reason, infrared detectors must be able to insulate the heat generated by the spacecraft itself, block heat rays from the sun, earth, satellite protrusions, etc., and keep the detector body in the cold space of outer space. It is installed through a radiant cooling device that ensures the target temperature by radiating. Therefore, such a radiation cooling device is composed of means for thermally insulating the infrared detector body and the spacecraft, and means for blocking unnecessary heat rays from the outside.

However, in the above-mentioned radiation cooling device, with the recent demand for larger space vehicles, the protruding parts of the solar battery paddles or antenna devices have become larger.
Since the cold space that can be secured is limited, efficient heat dissipation becomes difficult and reliable temperature control may not be possible.

(Problems to be Solved by the Invention) As described above, in the conventional radiation cooling device, it is difficult to secure a sufficient cold space in outer space, and there is a fear that reliable temperature control may not be possible.

This invention was made in view of the above circumstances, and aims to provide a radiation cooling device that has a simple configuration, secures a wide range of cold space, and realizes efficient temperature control. purpose.

[Structure of the Invention] (Means for Solving the Problems) The present invention includes a first heat reflector supported by a spacecraft and having a plurality of openings facing cold spaces in different regions; a first cooling body housed in a first heat reflector and providing thermal insulation from the spacecraft; and transporting heat from the first cooling body to at least one of the plurality of openings. a first heat transporting and heat dissipating means that radiates heat; a second heat reflector supported by the first cooling body and disposed corresponding to the plurality of openings; and this second heat reflector. a second cooling body supported by the cooling body and to which the object to be cooled is attached; and a second heat generating body that transports the heat of the second cooling body to at least one of the plurality of openings and radiates the heat. A radiation cooling device is constructed by including a transport heat dissipation means.

(Function) According to the above configuration, the heat of the spacecraft is transported to the plurality of openings disposed facing each other in cold spaces in different regions via the first cooling body and the first heat transport means. Heat is radiated. Further, the heat of the object to be cooled is transported to the plurality of openings via the second cooling body and the second heat transport means, and is radiated. Therefore, it becomes possible to secure a wide opening area in the cold space by the plurality of openings arranged separately. This ensures reliable heat dissipation and realizes efficient temperature control.

(Example) Hereinafter, an example of the present invention will be described in detail with reference to the drawings.

FIG. 1 shows a radiation cooling device according to an embodiment of the present invention, in which reference numeral 10 denotes an outer heat reflector, which is attached to a spacecraft (not shown). This outer heat reflector is provided with first and second openings 10a and 10b corresponding to different cold spaces. These first and second openings 1'Oa, 1
For example, in the case of a spacecraft 30 flying in a sun-synchronous orbit as shown in FIG. This corresponds to the different regions X and Y cold spaces that exist between them.

In addition, a through hole 10c for infrared detection is formed in the outer heat reflector 10 at approximately the center thereof, corresponding to the earth, and a hole 10c for infrared detection is formed in the outer heat reflector 10 to insulate heat from the spacecraft 30, corresponding to the through hole 10. A first cooling body 11 is disposed via a support member 12.

A first heat pipe 13 constituting a heat transport means is installed in this first cooling body 11 . The tip of the first heat pipe 13 extends into the first opening 10a, and a heat sink 14 is attached to the tip.

Further, an inner heat reflector 15 is attached to the first cooling body 11 via a support member 16. This inner heat reflector 1
5 has first and second openings 10a, 10 at both ends thereof.
b, and a second cooling body 17 is provided at the -end thereof.
is attached via a support member 18. An infrared detector 19 is attached to one end of the second cooling body 17 in correspondence with the through hole 10c of the outer heat reflector 10, and a second cooling body 17 constituting a heat transport means is attached to the other end. A heat pipe 20 is attached. The tip of the second heat pipe 20 extends into the second opening 10b, and the heat sink 21 is attached to the tip. In addition, the second heat pipe 2
A coupling member 22 for thermal coupling is attached to the intermediate portion of the heat pipe 0, and the base of a third heat pipe 23 is supported on this coupling member 22. The third heat pipe 23 has a distal end extending into the first opening 10a, and a heat dissipating body 2 at the distal end.
4 is attached.

In the above configuration, heat from the spacecraft 30 is transported to the first opening 10a via the first cooling body 11, the first heat vibrator 13, and the heat radiating body 14, and is radiated. At the same time, the heat from the infrared detector 19 passes through the second cooling body 17, the second heat vibrator 20, the coupling member 22, the third heat pipe 23 and the heat sink 21, 24 to the first and second openings. The light is transported to parts 10a and 10b and radiated. At this time, heat rays from the sun 31 are blocked by the outer heat reflector 10. This causes the infrared detector 19 to reach the desired value of 80~
The temperature is maintained at about 120°C.

In this way, the radiation cooling device has first and second openings 10a corresponding to different cold spaces in the outer heat reflector 10,
10b are provided separately, and the first and second openings 10
first and second cooling bodies 11.17 for a, 10b;
By configuring the spacecraft 30 and the infrared detector 19 to transport and radiate heat through the first to third heat pipes 13, 20, 23, it is extremely easy to secure the heat radiation opening area. Therefore, efficient temperature control is realized. According to this, since it is easy to secure the radiation aperture area, for example, there is no restriction on the mounting position of various mounting parts including the solar battery paddle mounted on the spacecraft 30, so the spacecraft It can also contribute to the simplification of handling including the design of 30.

Note that in the above embodiment, the first and second openings 10a, 1
Although the case where 0'b is provided has been described, the number is not limited to this, and a plurality of arrangements according to the number of regions of the cold space are possible depending on the application situation.

Further, in the above embodiment, the heat transferred to the first cooling body 11 is transferred to the first opening 10 via the first heat pipe 13.
a, and the heat transferred to the second cooling body 19 is transferred to the second and first
opening 10a.

Although the configuration is such that the heat is radiated by transporting it to the openings 10a and 10b, the present invention is not limited to this, and it is possible to selectively combine them depending on the amount of heat radiated.
A similar effect can be expected by transporting and dissipating heat to one side of b.

Further, in the above embodiment, the case where the application is applied to the infrared detector 19 has been explained, but the invention is not limited to this, and the spacecraft 3
It can be applied as a cooling means for various objects to be cooled that require various temperature controls mounted on the vehicle.

Therefore, it goes without saying that the present invention is not limited to the above embodiments, and that various modifications can be made without departing from the spirit of the invention.

[Effects of the Invention] As detailed above, the present invention provides a radiation cooling device that has a simple configuration, secures a wide range of cold space, and realizes efficient temperature control. can be provided.

[Brief explanation of the drawing]

FIG. 1 is a cross-sectional view showing a radiation cooling device according to an embodiment of the present invention, and FIG. 2 is a conceptual diagram showing the cold space region of the Earth View J satellite. DESCRIPTION OF SYMBOLS 10... Outer heat reflector, 10a, 10b... First and second openings, 10c... Through hole, 11... First cooling body, 12, 16.18... Support Part 13...
1st heat vibrator, 14, 21. 24... heat sink,
15...Inner heat reflector, 17...Second cooling body, 1
9... Infrared detector, 20... Second heat vibrator, 22... Coupling member, 23... Third heat pipe, 30... Spacecraft, 31... Sun, 32 ...
Earth. Applicant's agent Patent attorney Takehiko Suzue

Claims (1)

[Claims] a first heat reflector supported by a spacecraft and having a plurality of openings facing cold spaces in different regions;
a first cooling body that is housed in a heat reflector and provides thermal insulation from the spacecraft; and a first cooling body that transports the heat of the first cooling body to at least one of the plurality of openings. a first heat transport heat radiating means for radiating heat; a second heat reflector supported by the first cooling body and disposed corresponding to the plurality of openings; and supported by the second heat reflector. a second cooling body to which the object to be cooled is attached; and a second heat transporting and radiating body that transports and radiates the heat of the second cooling body to at least one of the plurality of openings. A radiation cooling device characterized by comprising means.