JPS60209399A - 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 (a) Technical Field of the Invention The present invention relates to an improvement in a radiation cooler for cooling an infrared detector onboard an artificial satellite to an operating temperature.

(To) Background of the Technology Photoelectronic detection elements made of multi-component semiconductors such as HgCdTθ are used in infrared detectors for infrared cameras mounted on recent resource exploration satellites. Although these have high sensitivity and fast response speed, in order to obtain reliable observation data, it is necessary to accurately introduce infrared rays emitted by the earth into the detector.

Therefore, there is a strong demand for the development of a radiation cooler having a position control mechanism for an infrared detector that is highly stable even in outer space in a vacuum and ultra-low temperature (4'K) environment.

(Q) Prior art and problems Figure 1 is a diagram for explaining the positioning and outline of the configuration of a radiation cooler, and Figure 2 is for explaining the position control mechanism of a conventional cooling plate equipped with an infrared detector. This is a diagram for (a)
is a side sectional view, and (to) is a Y-Y' arrow view. In Figure 1, l is the earth, 2 is the artificial satellite, 8 is the mirror, 4 is the infrared detector, 5 is the cooling plate, 5' is the heat radiation surface of the cooling plate, 6 is the reflector, 7 is the shield plate, and 8 is the earth. radiant heat, 8' indicates earth albedo, and 9 indicates infrared radiation. In FIG. 2, 10 is a case, 11 is a supporter, 12 is a cooling plate support line, and 15 is a pin.

40 is an infrared detector 4. Cooling plate 59 Reflector plate 6. A radiation cooler equipped with a sea 7 lead plate 7, and 60 each indicate outer space.

As shown in FIG. 1, the radiation cooler 40 is mounted on one side of the artificial satellite 2 and receives infrared rays 9 emitted from the earth 1 from the direction indicated by the arrow through a mirror 3 attached to the satellite 2. An infrared detector 4, a cooling plate 5 with the surface on which the detector 4 is attached facing the satellite 2 side and the opposite surface facing the outer space 50 side as a heat radiation surface 5', and the outer periphery of the cooling plate 5. A reflector plate 6 formed to expand from the end toward the outer space 50 side.
And, from the expanded outer peripheral end of the reflector plate 6, one side is further expanded toward the outer space 50 side, and the other side is formed so as to cover the cooling plate 5 and the reflector plate 6. It is equipped with the following. The detector 4 is connected to the heat radiation surface 5'.
The cooling plate 5 radiates heat toward outer space 50, which has an environmental temperature of 4°, and is cooled to an ultra-low temperature of 100', an upper operating temperature. Further, the earth's radiant heat 8 from the direction of the arrow E, which obstructs the cooling of the detector 4, is reflected by the reflector plate 6 and radiated toward the outer space 50 as shown by the arrow E'.
The earth albedo 8' from the direction of arrow F is the shield plate 7.
This makes it possible to stop the intrusion toward the direction of the cooling plate 5. Infrared rays 9 are observed by the detector 4, which is maintained at an operating temperature of about 100' by the radiation cooler 40, and are sent to an infrared image analysis device installed at a base on earth (not shown) and analyzed. The state of the earth's resources will be explored.

FIG. 2 is a diagram showing a conventional structure that adiabatically supports a cooling plate 5 including a heat sink to which the infrared detector 4 is attached in order to increase the cooling efficiency of the infrared detector 4. As shown in FIG.
It consists of eight cooling plate support lines 12 extending between supports 11 provided at each of the four corners on both sides of a case 10 formed to cover the case 10, and the length of each support line 12 is By adjusting 1, the force directions of the detector 4 attached to the cooling plate 5 are controlled in the direction of the arrows x-x', y-y7゜z-z' and the position of the force in the direction of the arrows R-R'.
is adjusted so that it is accurately incident on the detector 4. However, with this structure, when the satellite 2 is launched into space, it cannot cope with the environment (vacuum, 4'K) that is completely different from that on the ground. The Balanne collapses, making the position of the cooling plate 5 and, therefore, the infrared detector 4 unstable, and there is concern that the reliability of observation of the infrared rays 9 by the detector 4 will deteriorate.

(1) Purpose of the Invention The present invention was made in order to correct the above-mentioned conventional drawbacks, and its purpose is to provide a complete detector support mechanism for a radiation cooler that always operates stably even in outer space. be.

(θ) Structure and purpose of the invention According to the present invention, there is provided an infrared detector mounted on an artificial satellite to receive infrared rays from an object, and a heat dissipating surface that supports the detector and faces toward outer space. In a radiation cooler equipped with a cooling plate and a plurality of cooling plate support lines for adiabatically supporting the cooling plate in a case, a support line adjustment mechanism is attached to the cooling plate support line. This is achieved by providing a radiant cooler with special features.

(f) Examples of the invention Embodiments of the present invention will be described in detail below with reference to the drawings.

However, since the present invention relates to an improvement of a support mechanism for a cooling plate to which an infrared detector is attached, explanations of the overall configuration unrelated to the present invention and explanations that overlap with the previous explanations will be omitted as appropriate.

FIG. 8 is a diagram for explaining a support mechanism for a cooling plate provided with an infrared detector according to the present invention.

In this figure, the same parts as in FIGS. 1 and 2 are given the same reference numerals, and 21 is a boss provided on the case 10;
22 is a washer-shaped bearing, 28 is a coil μ spring, 24 is a support line adjustment screw, 25 is a seat nut, 30 is a washer-shaped bearing 22. Coil spring 28. Support line adjustment screw 24. Each of the support line adjustment mechanisms equipped with a seat nut 25 is shown.

As shown in FIG. 3, the cooling plate support mechanism according to the present invention has a washer-like bearing 22 mounted on each of the eight cooling plate support lines 12 supporting the five cooling plates shown in FIG. ．．
Coil spring 23. Support line adjustment screw 24. Nut with seat 25
It is characterized by the addition of a support line adjustment mechanism 80 comprising the following. The adjustment mechanism 30 includes a washer-shaped bearing 22 whose one side is in contact with a boss 21 provided in the case 10, and one end which passes through the center of the bearing 22 and approaches the cooling plate 5. A support wire adjustment screw 24 having a cooling plate support wire 12 fixed thereto and a seat nut 25 screwed into the other end, and a support wire adjustment screw 24 that surrounds the adjustment screw 24 and is connected to the bearing 22 and the seat nut 2.
5, the cooling plate support wire 12 moves the cooling plate 5 in the direction of the arrow H-H' force.

By sequentially performing this operation on all eight support wires 12, the cooling plate 5 (see the previous figure 2) has the following characteristics: X-X', Y-Y', z-zzj, R-R' The infrared detector 4, which moves in each direction and is attached to the cooling plate 5, is set at a position where it can accurately receive the infrared rays 9 incident from the satellite 2 in the six directions of arrows. In addition, the outer space 50 due to the environmental difference between the ground and the outer space 50
The positional deviation of the detector 4 caused by loosening or overtensioning of the support wire 12 is absorbed and alleviated by the coil spring 28 provided in the support wire adjustment mechanism 80. The phenomenon of positional deviation caused by this is almost completely avoided, and the infrared detector 4 can exhibit stable functions over a long period of time.

(2) Effects of the Invention As explained in detail above, the radiation cooler of the present invention has a great effect in that the position and attitude of an infrared detector mounted on an artificial satellite can be accurately maintained in space as well as on the ground. It is what it is.

[Brief explanation of drawings]

Fig. 1 is a diagram for explaining the configuration of a radiation cooler, Fig. 2 is a diagram for explaining a position control mechanism of a cooling plate equipped with a conventional infrared detector, and Fig. 8 is an infrared radiation cooler according to the present invention. It is a figure for explaining the position control mechanism of the cooling plate to which the detector was attached. In the drawing, 1 is the earth, 2 is the satellite, 8 is the mirror, and 4
is an infrared detector, 5 is a cooling plate, 6 is a reflector, 7 is a shield plate%8 is earth radiant heat, 9 is infrared rays, 10 is a case, 1
1 is a supporter, 12 is a cooling plate support line, 15 is a pin, 21
is a boss provided on the case 10, 22 is a washer-shaped bearing, 28 is a coil spring, 24 is a support wire adjustment screw, 25 is a seat nut, 8° is a support wire adjustment mechanism, 40 is a radiation cooler, 50 is outer space are shown respectively. 11ff1 0 Figure 2 (CI) (b) ite=ni≠=- JP-A-Sho GO-209399 (4) Figure 3 1) 11\-beat fl+': 1 at -m--

Claims (1)

[Claims] An infrared detector mounted on an artificial satellite to receive infrared rays from a target, a cooling plate that supports the detector and has a heat radiation surface facing toward outer space, and the cooling plate is heat-insulated within a case. What is claimed is: 1. A radiation cooler comprising a plurality of temporary cooling support lines for supporting the cooling plate, characterized in that a support line adjustment mechanism is attached to the cooling plate support line.