JPH042880Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to heat radiation control of a triaxially orbiting artificial satellite.

[Conventional technology]

Conventionally, in orbiting satellites that perform 3-axis stability control, it is common to radiate heat using the surface that is less irradiated with sunlight, but if the amount of heat radiated increases and the area is insufficient, the 4th As shown in the figure, a heat dissipation surface 4 is extended to the top surface 3 as shown at 13, and heat is transported and dissipated there using a heat pipe or the like. In this case, to reduce the influence of sunlight, the surface should be
It was necessary to cover it with optical, solar reflector or silver-coated Teflon.

[Problem that the invention attempts to solve]

In the conventional heat dissipation control method described above, as the amount of heat dissipated from the satellite increases, the area of the heat dissipation plate must be increased, and in order to avoid mechanical interference with the rocket's fairing, it is usually implemented as shown in Figure 4. Since the length is extended to the top surface, there are disadvantages as shown below.

Since various devices such as antennas are mounted on the top surface, there is a natural limit when considering interference with these devices, and it is not suitable for dissipating a high amount of heat.

When extending the heat sink toward the top, the center of gravity of the satellite is raised toward the top, and the distance from the separation surface between the satellite and rocket to the center of gravity becomes longer. If you create one, the weight of the satellite will increase.

If the heat sink is extended toward the top, the satellite will become vertically elongated and its mass properties will deteriorate.

The surface needs to be covered with optical, solar reflector, or silver-deposited Teflon, making it expensive and difficult to handle.

[Means for solving the problem] The radiator for a three-axis orbiting artificial satellite of the present invention is attached to the boom part of the solar array paddle, and is always oriented in the anti-sun direction by the rotation of the solar array paddle, thereby reducing heat radiation. A heat sink whose heat dissipation surface is coated with a paint that increases the heat exchange rate and prevents heat input due to reflection of sunlight by the earth, a heat pipe or liquid loop that transports heat from the satellite to the heat sink, and a heat pipe or liquid loop that transports heat from the satellite to the heat sink. It has a rotary joint for connecting the loop to a rotating heat sink, and a thermal blanket for blocking heat input from the sun-irradiated surface of the heat sink.

In general, solar array paddles are designed to avoid the effects of shadows from equipment mounted on each side of the satellite.
The boom keeps the satellite away from the entire satellite to a point where its shadow does not fall on the solar cell surface. The space between the satellite body and the solar array paddle connected by a boom is usually a dead space.
The present invention makes effective use of this space. Furthermore, since the solar cell paddle is controlled so that the cell surface always faces the sun, providing the heat dissipation surface in the anti-sun direction prevents sunlight from irradiating it, allowing efficient heat dissipation.

〔Example〕

Embodiments of the present invention will be described with reference to the drawings.

Figure 2 is a conceptual diagram of a satellite equipped with an embodiment of the radiator for three-axis orbiting satellites of the present invention, Figure 1 is a detailed diagram of the radiator shown in Figure 1, and Figure 3 is a diagram of the satellite being launched. It is a figure showing a solar battery paddle storage state of.

A pipe-shaped liquid loop heat generating section 8 for extracting heat from the heat generating device 7 is provided on the back surface of the satellite heat dissipating surface 4, and a rotating section protrudes from the satellite heat dissipating surface 4. The rotary joint section 10 includes a liquid loop heating section 8
It connects the fixed part and the rotating part. The solar array paddle 2 is normally folded so as to fit into the fairing of the rocket at the time of launch, as shown in FIG. For this purpose, the boom is provided with a hinge. The flexible part 5 is for bending the pipe of the liquid loop heating part 8 in accordance with the movement of this hinge. The solar battery paddle drive device 9 is a device for always pointing the solar battery paddle 2 toward the sun, and is provided in a typical three-axis control satellite. The solar array paddle 2 includes a heat sink 1 oriented in the anti-sun direction, and transmits heat transported to the heat sink 1 via a liquid loop heat generating section 8, a rotary joint section 10, and a liquid loop flexible section 5. A liquid loop heat radiating section 6 is provided that radiates heat into outer space. The heat dissipation plate 1 is coated with a paint (for example, white paint) that increases the thermal emissivity and prevents heat input due to sunlight reflected by the earth (albido). Also, sunlight is always on the heat sink 1
Since the back surface of the heat sink 1 will be irradiated with sunlight, a thermal blanket is attached to the back surface of the heat sink 1 to block sunlight input.

[Effect of idea]

As explained above, the present invention radiates the amount of heat that cannot be radiated by the satellite heat radiating surface using the heat radiating plate installed in the boom section of the solar array paddle, thereby preventing mechanical interference with equipment on each surface of the satellite. A large amount of heat can be dissipated without any consideration, and since it is folded together with the solar array paddle at the time of launch, there are no mounting problems, and since the heat dissipation surface is always oriented in the anti-solar direction, the surface of the heat dissipation surface is , it can be constructed at low cost by simply applying paint, and there is no need to use optical, solar reflector, or silver-deposited Teflon to reduce the effects of sunlight irradiation, unlike conventional heat dissipation surfaces, and the design has been changed. This has the effect of being able to respond flexibly even when changing the area due to reasons such as changing the area.

[Brief explanation of the drawing]

Figure 1 is a conceptual diagram of an artificial satellite equipped with the heat sink shown in Figure 2, Figure 2 is a detailed diagram of an embodiment of the heat sink for a three-axis orbiting satellite of the present invention, and Figure 3 is a conceptual diagram of an artificial satellite equipped with the heat sink shown in Figure 2. FIG. 4 is a diagram showing the solar battery paddle storage state at the time of launch, and is a diagram showing a conventional heat sink. 1... Heat sink, 2... Solar battery paddle, 3...
Top surface and equipment, 4... Satellite heat radiation surface, 5... Liquid loop flexible part, 6... Liquid loop heat radiation part, 7... Heat generating device, 8... Liquid loop heat generating part,
9...Solar battery paddle drive device, 10...Rotary joint section, 11...Folded solar battery paddle, 12...Rocket fairing.

Claims (1)

[Claim for Utility Model Registration] In a three-axis orbiting artificial satellite, the first surface is always oriented in the anti-sun direction by the rotation of the solar array paddle, which is attached to the boom part of the solar array paddle, and further increases the thermal emissivity. a heat sink whose first surface is coated with a paint that prevents heat input due to reflection of sunlight by the earth; a heat pipe or liquid loop for transporting heat from the satellite to the heat sink; and a heat pipe or liquid loop for transporting heat from the satellite to the heat sink. or a rotary joint part inserted in the middle of the liquid loop for thermally connecting the satellite and the heat sink via a heat pipe or the liquid loop regardless of the rotational movement of the heat sink; a second surface opposite to the first surface;
A heat sink for a triaxially orbiting artificial satellite, the heat sink having a thermal blanket attached to the surface of the second surface to block heat input from sunlight irradiated onto the second surface.