JPH0139280Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Technical Field of the Invention] This invention relates to a thermal control device that adjusts heat input and output to an artificial satellite flying in outer space.

A typical method for supplying power to an artificial satellite is by using solar cells. As the size of artificial satellites increases, the amount of power required also increases. Therefore, a method is being adopted in which solar cells are attached to several panels, launched in a folded state, and then expanded in orbit to generate electricity. Until the solar panels are deployed and power is supplied, electricity supplied from batteries inside the satellite is used, but because the electricity is small, the amount of heat generated from electronic equipment is small, and the temperature inside the satellite is low. Impairs adjustment. Therefore, during this period, it is necessary to cover the top surface of the heat sink on the outside of the satellite with a heat control material that absorbs heat from the outside and prevents it from escaping. On the other hand, after the solar cells are deployed, the power will increase and the amount of heat generated will be excessive, so this cover must be removed.

[Prior art]

Conventionally, there have been devices of this type as shown in FIGS. 1 to 3. Figure 1 shows the satellite main body 1, the folded solar panel group 2, the heat control cover 3, and the heat radiation plate 4 at the time of launch, and Figures 2 and 3 show the solar battery panels 5 to 5 on orbit. FIG. 8 is a front view and a plan view showing a state in which the device 8 is unfolded. In the figure, each solar battery panel 5 to 8 is connected by a hinge 9, and after deployment, the solar battery panels 5 to 8 are connected by the hinge 9 so that the solar battery panel group 2 is aligned in a straight line.
-8 is fixed. The heat control cover 3 is a flat plate with a heat control material glued or painted, and the solar cell panel 8
installed on. By the way, in the folded state of the panel as shown in FIG. 4, the heat control cover 3 is on the heat sink 4 and covers the heat sink 4. As shown in FIGS. 2 and 3, when the solar panels 5 to 8 are expanded,
The heat control cover 3 moves together with the solar panel 8, and there is nothing on the surface of the heat sink 4 to prevent heat radiation, so that it can perform its original function.

Since the conventional device is configured as described above, the weight of the solar cell panel group 2 is increased. In addition, since only the weight of the outer solar panel 8 increases, the weight balance of the solar panels 5 to 8 deteriorates, making it difficult to smoothly deploy the solar panels 5 to 8. Also, due to the arrangement of the satellite onboard equipment, if the heat control cover 3 is moved from its current position to the position shown in Figure 6, the heat control cover 3 and the solar panel 7
It collides and becomes impossible to develop. Further, in the panel storage state, as shown in FIG. 7, heat Q is radiated from the gap in the heat control cover 3, resulting in a disadvantage that the efficiency is not good.

[Summary of the idea]

This invention is intended to eliminate these drawbacks, and provides an efficient heat control device without directly attaching the heat control cover 3 to the solar panels 5 to 8.

[Example of idea]

An embodiment of this invention will be described below.
Figure 8 shows the roll-up heat control cover 10 and the satellite body 1.
and the positional relationship with the solar panel group 2. As shown in FIG. 9, first plates 1 and 11 are attached to the satellite body 1. A leaf spring 12 is attached perpendicularly to the first plates 1, 11 at both ends of the first plates 1, 11. When the leaf spring 12 is in a free state, it curls into a coil shape as shown by the dotted line in the side view of FIG. The other end of the leaf spring 12 is attached to the second plate 2,13. When the leaf spring 12 is stretched, the two leaf springs 12 and the first
The plates 1 and 11 and the second plates 2 and 13 form a rectangular frame. A heat control sheet 14 is adhered to this frame. Furthermore, the leaf spring 12 is firmly sandwiched and fixed by the third plates 3, 15 and the fourth plates 4, 16. The slide pin 1 is attached to the second plate 2, 13.
A pin hole 20 is drilled into which a slide pin 17 can be inserted, and by inserting a slide pin 17, the leaf spring 12 is held in an expanded state. The slide pin 17 is inserted into the pin hole 20 via the holder 18 and spring 19. The slide pin 17 is held down by a force F from the holding and releasing position, and by being released from the force F from the holding and releasing device, the slide pin 17 comes out of the pin hole 20, and the second plates 2, 13 are released. The leaf spring 12 and the heat control sheet 14, which were in a free state and stretched out on the flat plate, are deformed into a cylindrical shape by the force of the leaf spring 12. Therefore, the flat sheet for heat control material 1
The heat radiating plate 4 covered by the spacer 4 is exposed to outer space and can perform a heat radiating function.

The above description has been made for the case where the solar battery paddle group 2 and the heat radiation plate 4 are on the same surface, but this invention is not limited to this.
This function can be achieved even if the two are not on the same plane.

[Effect of idea]

As described above, according to this invention, since the heat control cover is not attached to the solar cell panel, the weight of the solar cell panel does not increase. Furthermore, since it does not impede the expansion of the solar cell panel, it can be mounted on a flat surface with a heat radiation plate regardless of the orientation of the solar cell panel. Since it has a structure consisting only of a heat control sheet and an outer frame, it has the advantage of being lightweight.

[Brief explanation of the drawing]

Figures 1, 2, and 3 are schematic front and plan views of the satellite body, solar panel, and conventional thermal control cover in the folded and unfolded states, respectively, and Figure 4 is the folded state. Detailed drawing of 5th
The figure is a schematic diagram of the state in which the mounting position of the heat control cover has been changed, Figure 6 is a schematic diagram explaining that it cannot be deployed in the case of Figure 5, and Figure 7 is a schematic diagram of the state where the heat control cover has been installed. An explanatory diagram showing that heat is radiated, Fig. 8 is a three-sided view of an embodiment of this invention, Fig. 9 is a three-sided view of the main part of Fig. 8, and Fig. 10 is a view around the slide pin in one embodiment. FIG. In the figure, 1 is the satellite body, 2 is a group of solar panels, 4 is a heat radiation plate, 5, 6, 7, 8 are solar panels, 9 is a hinge, 11 is the first plate 1, 12
13 is a second plate 2, 14 is a heat control sheet, 15 is a third plate 3, 16 is a fourth plate 4, 17 is a slide pin, 18 is a holder, and 19 is a spring. In the drawings, the same or corresponding parts are denoted by the same reference numerals.

Claims (1)

[Scope of utility model registration request] Parallel first and second plates attached to the satellite body; and attached to both ends of the first and second plates in an extended state; at least two leaf springs forming a rectangular frame surrounding a heat radiating plate having a heat radiation plate; a heat control sheet attached to the rectangular frame;
The third and fourth plates are clamped and fixed between the second plate and a holding and releasing mechanism that holds and releases one end of the leaf spring. A heat control device characterized in that the heat control sheet is removed from the heat radiation plate by the action of a spring.