JPS6092200A - Radiational cooler - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION (α) Technical Field of the Invention The present invention relates to improving the performance of a radiation cooler that cools an infrared detector mounted on an artificial satellite by heat radiation into outer space.

The infrared detector used for this purpose uses elements such as T(f, odlT4, etc.), which have high sensitivity and fast response speed, but in order to maintain the infrared rays that enter the detector in the middle of the incident path, the infrared rays that enter the detector must be It is necessary for the infrared rays to reach the detection element of the detector without being obstructed by the invading outgas.For this reason, the infrared rays entering the detector must be cooled with good cooling efficiency and the infrared rays incident on the detector can be removed from the infrared rays. There is a strong demand for the development of high-performance radiation coolers.

(C) Node Z between the conventional technology and the 11th diagram is a diagram to clarify the configuration and function of a conventional radiation cooler and infrared detector, (α) is a side sectional view of the radiation cooler, (b ) is a sectional view of an infrared detector attached to a radiation cooler, and (C) is a partially enlarged sectional view taken in the direction of arrow As. In the figure, 1 is the satellite body, 1' is the boundary plate, and 2
As shown in FIG. 1(b), the sensing element 11, nitrogen 12,
An infrared detector equipped with an IJ-hard terminal 13, 3 a cooler, 3' a heat dissipation surface, 4 a reflector, 5 a sheet, 9 an infrared ray, 14 an outgas, and 20 a A heat-insulating fixing mechanism consisting of a fixing plate 6, a heat-insulating spacer 7, and a nut 8 is shown.

As shown in Figure 1, the radiation cooler is disposed on a boundary plate 1' provided on one side of the satellite main body 1 (parallel to the vertical line of the earth and on the side of the satellite that detects infrared radiation). a cooler 8 to which a container 2 is attached and whose opposite side faces toward outer space; a reflector 4 extending toward outer space from the outer peripheral end of the cooler 3; It consists of a plate 4 and a shield plate 5 which is formed to cover the cooler 3 and is fixed with a nut 8 via a heat insulating spacer 7 to a fixed plate 6 which is vertically planted on the boundary plate 1'. The radiation cooling mechanism and the mechanism are moved to predetermined positions on the satellite body 1.
A heat insulating fixing mechanism 20 consisting of the fixing plate 6, the heat insulating spacer 7, and the nut 8 fixed at a constant distance from the
It is made up of.

Although not shown, the infrared rays 9 that are caught by the camera mechanism attached to the satellite main body 1 and incident from the direction of the arrow X pass through the window 12 attached to the infrared detector 2 and reach the detection element 11. 11 causes a photoelectric reaction corresponding to the photons of the infrared rays 9. The photoelectric reaction is then sent via the lead terminal 13 to an infrared analysis processor (not shown) and analyzed. In this way, the situation of infrared rays on the earth can be adjusted to a standard temperature of 20W (293K) using the conventional structure.
) is maintained at an extremely low temperature (10
0K) from the gap 9 between the shield plate 5 constituted by the heat insulating spacer 7 of the heat insulating fixing weave 20 and the fixing plate 6 to avoid heat conduction to the radiation cooler at 0K). The outgas 14 generated by the gas enters the nitrogen 1 of the detector 2 as shown by arrows B and B'.
It adheres to the heat dissipation surface 3' of the cooler 3, the reflection plate 4, and the shield plate 5, inhibiting their heat radiation and reflection functions, and inhibiting the radiation cooling. This resulted in deterioration of the cooling function of the device.

Note that the figures used in the above description are all side sectional views, so only the top and bottom two sides are shown, but the present radiation cooler has the same structure on all four sides, top, bottom, left and right.

(d) Object of the Invention The present invention has been made to correct the above-mentioned conventional drawbacks, and an object of the present invention is to provide a structure for blocking outgas from entering the radiation cooler from the satellite main body side.

(e) Structure and object of the invention According to the present invention, a radiation cooling mechanism equipped with a cooler and a reflector for cooling an infrared detector mounted on an artificial satellite by thermal radiation into outer space, and Provided is a radiation cooler comprising an adiabatic fixing mechanism for fixing a cooling mechanism to a predetermined position of a penal spacecraft, characterized in that a gap in the adiabatic fixing mechanism is sealed against intrusion of outgas. This is achieved by

ω　Embodiments of the invention Embodiments of the present invention will be described in detail below with reference to the drawings.

FIG. 2 shows the structure and structure of the radiation cooler according to the present invention (4 is a partially enlarged sectional view of zone A in the direction of arrows).

In the same figure, the same parts as the previous one are given the same symbols, and 5' is the L-shaped fin with the number installed on the shield plate 5,
6' indicates a T-shaped fin provided on the fixing plate 6, and jO indicates an outgas blocking tape. In the explanation of FIG. 2, parts that overlap with the explanation of FIG. 1 are omitted as appropriate to avoid complexity.

As shown in FIG. 2, in the radiation cooler of the present invention, a gap G between a shield plate 5 constituted by a heat insulating spacer 7 and a fixing plate 6 is formed between an L-shaped fin 5' provided on the shield plate 5 and a fixing plate 6. The structure is such that the entire circumference of the gap 6 is sealed with an outgas blocking tape 10 so as to span both T-shaped fins 62 provided in the gap 6.

Therefore, the satellite main body 1 may leak out and enter through the gap G, adhere to the infrared detector 2, and obstruct the transmission of infrared rays 9, or adhere to the heat dissipation surface 3' of the cooler 3, causing the cooling 'a3 In addition, the reflective surfaces of the reflector plate 4 and shield plate 5 may interfere with the cooling effect of the reflector plate 4 and the shield plate 5. 10 completely prevents intrusion from the WRG. Note that tape 0 has a wide usable temperature range, has excellent low-temperature properties, and is made of polyimide film with silicone, for example, which has a high heat insulating effect. A material coated with a type of adhesive is used.

(F) Effects of the Invention As explained in detail above, the radiation cooler of the present invention has a heat insulation gap provided between the satellite body and the radiation cooler by attaching an outgas insulation tape with a simple configuration. This has a great effect in that it can accurately prevent outgas from entering the radiation cooler.

[Brief explanation of the drawing]

1 is a diagram for explaining the structure and function of a conventional radiation cooler and an infrared detector, and FIG. 2 is a diagram for explaining the structure of a radiation cooler according to the present invention. In the drawing, 1 is the satellite body, 2 is the detection element 11,
chamber 12, an infrared detector equipped with lead terminals 13, 3 a cooler, 4 a reflector, 5 a shield plate, 6 a fixing plate, 7
is a heat insulating spacer, 8 is a nut, 9 is an infrared ray, 10 is an outgas blocking tape, 11 is a detection element, 12 is nitrogen, ]3 is a lead terminal, ]4 is an outgas, 20 is a fixing plate 6, a heat insulating spacer 7, a nut 8 The adiabatic fixing mechanism consisting of the following is shown. Figure 1 (a) r-jinichiichi (C) Figure 2

Claims (1)

[Claims] A radiation cooling mechanism equipped with a cooler and a reflector that cools an infrared detector mounted on an artificial satellite by heat radiation into outer space, and an adiabatic fixing mechanism that fixes the radiation cooling mechanism to a predetermined position on the artificial satellite. 1. A radiant cooler comprising: a radiant cooler comprising: a gap in the adiabatic fixing mechanism is sealed against intrusion of outgas.