JPH0539100A - Light collecting radiator for space - Google Patents

Abstract

PURPOSE:To reduce consumption of main fuel consumed at launching a space flying body and orbital correction fuel consumed at correcting the orbit by reducing the developed area outside the body to nearly half so as to reduce air resistance of the space flying body. CONSTITUTION:Visible radiation in the sunlight 2 is reflected on a reflective film 24 through a radiative film 25. Infrared radiation R in the sunlight 2 is absorbed by the radiative film 25 to be converted to heat, and radiated from the radiative film 25 as heat. Meanwhile, heat carried by radiative medium flowing in a radiating pipe 27 is transmitted to a radiative film 25 through a base plate 23 and the reflective film 24, and radiated from the radiative film 25.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a space heat radiator mounted on a spacecraft.

[0002]

2. Description of the Related Art In recent years, research and development on space shuttles and other spacecraft have been advanced. The spacecraft is generally provided with a light collector that collects sunlight emitted from the sun, and a radiator that radiates extra heat generated by the spacecraft to outer space.

An example of the above will be described with reference to FIG.
Is a concentrator for concentrating the sunlight 2, which is formed by combining a large number of mirror panels 5 in a parabolic shape and forming a passage hole for the sunlight 2 in the center thereof. A large condensing mirror 6 is arranged outside toward the sun, a reflecting mirror 7 is arranged at a focal point of the condensing mirror 6, and a rear side of the passage hole 4 of the condensing mirror 6 is arranged. And a cylindrical light receiver 8.

As shown in FIG. 4, the light receiver 8 has an introduction hole 9 for the sunlight 2 which is connected to the passage hole 4 of the condenser mirror 6 at the center of the end surface on the condenser mirror 6 side. In addition, a large number of long U-shaped heat collecting tubes 10 are arranged all around the cylindrical surface,
A gas 11 as a heat medium is circulated inside the heat collecting tube 10 to collect heat from solar heat. Each heat collecting tube 10 of the light receiver 8 includes a gas turbine engine 13 and a gas loop 12 for power generation shown in FIG. Connected through.

The gas turbine engine 13 includes a turbine 14 which is rotated by a gas 11 flowing in a gas loop 12 shown in FIG. 5 to drive a generator 17, and a compressor 18 which is connected to a shaft 15 of the turbine 14 to compress and circulate the gas 11. And a heat exchanger 21 arranged between the turbine 14 of the gas loop 12 and the compressor 18. In the heat exchanger 21, the heat of the gas 11 that cannot be converted into power and remains in the fluorocarbon 22 flows through the fluorocarbon loop 19.
By exchanging heat with the (heat medium) and radiating the heat to the outer space from the radiator 20, the gas 11 is lowered in temperature and the compression efficiency of the compressor 18 is improved. The radiator 20 shown in FIG. 3 is a large one having substantially the same surface area as the condenser mirror 6. When the sunlight 2 is received, the temperature rises and the heat radiation function deteriorates. It is set up.

In such a spacecraft 3, the sunlight 2 received by the condenser mirror 6 is reflected by the reflection mirror 7 and introduced into the light receiver 8 through the passage hole 4 and the introduction hole 9, as shown in FIG. Heating the gas 11 flowing through the heat collecting tube 10 shown in
The heated gas 11 rotates the turbine 14 of the gas turbine engine 13 shown in FIG. 5 to drive the generator 17 and the compressor 18, which generates electricity. On the other hand, the heat that cannot be converted into power and remains in the heat exchanger 21 is the Freon 22 which is a heat medium circulating in the Freon loop 19.
After the heat is exchanged with the radiator, the heat is radiated from the radiator 20 to the outer space.

[0007]

By the way, as described above, the condenser mirror 6 and the radiator 20 shown in FIG. 3 employed in the conventional spacecraft 3 are large-sized ones having substantially the same surface area. As a result, extra air resistance is applied even when the orbit is corrected in and around the atmosphere.
Fuel consumption of spacecraft for orbital correction at

The present invention has been made in view of the above situation, and the deployment area outside the fuselage can be almost halved, thereby reducing the system weight and air resistance, and the main fuel at the time of launch and the trajectory correction consumed at the time of trajectory correction. It is an object of the present invention to provide a space condensing radiator capable of reducing the consumption amount of fuel for use in space.

[0009]

According to the present invention, a reflective film having a high reflectance of sunlight is formed on the surface of a substrate, and visible light of sunlight is transmitted through the surface of the reflective film, but infrared light is transmitted. The present invention relates to a space condensing radiator in which a heat radiation film for absorbing and releasing heat is formed, and a heat radiation tube for circulating a heat radiation medium is attached to the back surface of the substrate.

[0010]

Function: Visible light of sunlight passes through the heat dissipation film and is reflected by the reflection film.

Infrared light of sunlight is absorbed by the radiation film and is emitted from the heat radiation film as heat.

On the other hand, the heat carried by the heat dissipation medium flowing through the heat dissipation tube is transferred to the heat dissipation film through the substrate and the reflection film and is dissipated from the heat dissipation film.

[0013]

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

1 and 2 show an embodiment of the present invention.

In the figure, the same parts as those shown in FIGS. 3 to 5 are designated by the same reference numerals, and the description will be made with reference to FIG.

A reflective film 24 such as aluminum or silver having a high reflectance of sunlight is formed on the surface of a substrate 23 made of aluminum, and visible light such as SiO, SiO ₂ or Teflon passes through the surface of the reflective film 24. A heat dissipation film 25 having a function of absorbing the infrared light R and radiating heat is formed to form a condensing heat dissipation surface 26 on the front surface side of the substrate 23, and further, a freon loop 19 is formed on the back surface of the substrate 23. The heat radiation tube 27 is flattened so that the contact area with the substrate 23 becomes large, and then bonded to form the light collecting heat radiation panel 28.

The light collecting and radiating panel 28 is combined to form a parabola type light collecting and radiating body 29, and the light collecting and radiating body 2 is formed.
The back side of 9 is the honeycomb 3 of aluminum, CFRP, or the like.
0 and the skin plate 31 and other lightweight structural members 32 are used for supporting and reinforcing. At this time, a gap 33 is formed between the radiating pipes 27 so that the honeycomb 30 does not come into direct contact with them.

Further, the light receiver 8 is disposed at the focal point of the light collecting and radiating body 29, and the pipe of the gas loop 12 is passed through the inside of the support pipe 34 for supporting the light receiving body 8 on the light collecting and radiating body 29.

Next, the operation will be described.

When the light collecting and radiating surface 26 of the light collecting and radiating body 29 is directed to the sun, visible light of the sunlight 2 is transmitted through the heat radiating film 25 of each light collecting and radiating panel 28 and reflected by the reflecting film 24. The light is collected in the light receiver 8 arranged at the focal point of the condenser heat radiator 29.

On the other hand, the infrared light R of the sunlight 2 is absorbed by the heat radiation film 25 of the condensing heat radiation panel 28 and emitted to the outer space as heat. Therefore, the temperature of the reflective film 24 and the substrate 23 is prevented from rising due to the energy of the infrared light R.

The energy of visible light collected in the light receiver 8 heats the gas 11 flowing through each heat collecting tube 10 in the light receiver 8, and the gas turbine engine 13 is heated by the heat energy of the heated gas 11. Is rotated,
The compressor 18 and the generator 17 are driven.

The gas 11 which has driven the gas turbine engine 13 is thereafter deprived of the residual heat energy in the heat exchanger 21 by the freon 22, compressed by the compressor 18, and sent to the light receiver 8 again.

On the other hand, the chlorofluorocarbon 22 which has obtained heat from the heat exchanger 21
Flows through the flon loop 19 and is sent to the heat radiation tube 27 on the back surface of the light collecting and heat radiation panel 28.

The heat of the fluorocarbon 22 flowing through the heat radiation tube 27 is transferred to the heat radiation film 25 through the substrate 23 on which the heat radiation tube 27 is installed and the reflection film 24, and is radiated from the heat radiation film 25 to outer space.

Thus, the reflective film 24 is formed on the surface of the substrate 23.
The heat radiation film 25 is formed, and the heat radiation tube 27 is attached to the back surface of the substrate 23 to form the heat radiation radiator 29 having the functions of both the condenser and the radiator. The amount of the main fuel at the time of launching and the fuel for orbital correction consumed at the time of orbital correction can be reduced because the system weight and the air resistance of the spacecraft 3 are reduced almost by half.

Further, since the light collecting and heat radiating are performed on the same light collecting and radiating surface 26, it is easy to mount the spacecraft 3 so as not to affect the heat, and the light collecting and radiating body 29 is attached from the back side. As the structural member 32 that supports and reinforces, it is possible to use CFRP or the like, which has a low heat dissipation property but is lightweight, so that it is possible to further reduce the weight.

Although the embodiment of the present invention has been described above, the present invention is not limited to this embodiment, and needless to say, various structures can be adopted without departing from the scope of the invention.

For example, in the embodiment, the gas turbine engine is shown as an engine for power generation, but the engine is not necessarily limited to this, and other engines such as a Stirling engine may be used.

[0030]

According to the present invention, the deployment area outside the fuselage can be halved, which reduces the air resistance of the spacecraft and consumes the main fuel that is consumed when the spacecraft is launched and the orbital correction. It is possible to reduce the amount of fuel for orbit correction.

[Brief description of drawings]

FIG. 1 is an overall schematic view of an embodiment of the present invention.

FIG. 2 is a partially enlarged sectional view of FIG.

FIG. 3 is an overall schematic view of a conventional spacecraft.

FIG. 4 is an enlarged perspective view of the collector body of FIG.

5 is a schematic diagram of the gas turbine engine of FIG.

[Explanation of symbols]

 2 Sunlight 22 Freon (heat medium) 23 Substrate 24 Reflective film 25 Radiating film 27 Radiating tube R Infrared light

Claims (1)

[Claims] 1. A heat dissipation device, wherein a reflective film having a high reflectance of sunlight is formed on the surface of a substrate, and visible light of sunlight is transmitted through the surface of the reflective film but infrared light is absorbed and heat is released. A space condensing radiator, wherein a film is formed and a radiation tube for circulating a radiation medium is attached to the back surface of the substrate.