JPH02267491A - Radiator - Google Patents

Abstract

PURPOSE:To reduce the weight of, to simplify a radiator and to automatically adjust heat radiation amount by providing cooling tubes made of shape memory alloy formed spirally or in a zigzag state in a repeating shape, and a heat sink plate made of aluminum foil extended between adjacent cooling tubes. CONSTITUTION:Since cooling tubes 8 are formed of shape memory alloy, they are contracted at a set temperature or lower (a), and extended at the set temperature or higher (b). A heat sink plate 9 made of aluminum foil extended between adjacent tubes 8 is extended or contracted upon extension of contraction of the tube 8, its surface area is varied, and cooling capacity of the radiator is varied in response to the variation. That is, the cooling capacity is increased due to extension when medium of high temperature flows in the tubes 8, and decreased due to contraction when medium of low temperature flows in the tubes 8. The adjustment of the capacity is automated only by the deformation of the alloy due to thermal load, and a valve and a control system are not required to be provided as a conventional one.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a radiator for a heat exchange system of a space station.

[Conventional technology]

Figure 4 shows a system diagram of a conventional space station heat exchange system. In the figure, 1 is an evaporator, 2 is a heat exhaust pipe, 3 is a radiator, 4 is a return pipe, and 5 is a pump. This system is filled with a medium 7 or ammonia. Note A indicates outside the spacecraft, and B indicates inside the spacecraft. Heat inside the spacecraft is collected by an evaporator 1. At this time, the medium is vaporized and sent to the radiator 3 outside the spacecraft, where it is radiatively cooled and liquefied. It reaches the pump 5 via the return pipe 4, where it is pressurized and sent to the evaporator 1 again.

Since the amount of heat generated within the spacecraft is naturally not constant, the amount of heat radiated from the radiator 3 needs to be adjusted. FIG. 5 shows a system diagram of a conventional heat radiation amount adjusting device. 6 is a flow control valve, and 7 is a radiator, and the flow rate of the medium sent thereto is controlled by a flow control device 7 via the flow control valve 6.

[Problem that the invention aims to solve]

The configuration shown in FIG. 5 requires a plurality of radiators depending on the maximum value of the heat load, and also requires a flow control valve 6 and a control system 7 to adjust the radiators. This is not desirable for space equipment that wants to be as light as possible.

The present invention is a book that attempts to provide a radiator that is lightweight, simple, and automatically adjusts the amount of heat radiation.

[Means to solve the problem]

The present invention has solved the above problem, and consists of cooling pipes made of a shape memory alloy formed in a repeating shape such as a spiral or meandering shape, and a space between the cooling pipes (made of stretched aluminum foil). The present invention relates to a radiator equipped with a heat sink.

[Effect]

In the radiator of the present invention, the cooling tube is made of a shape memory alloy, so it expands and contracts in the direction of the center line of the spiral or meander depending on the temperature. As the cooling pipe expands and contracts,
The aluminum foil heat sink stretched between the cooling pipes is expanded and stored. When the temperature of the medium in the cooling tube is high, the cooling tube stretches and the heat sink spreads (9) and the amount of heat radiation increases, and when the temperature of the medium in the cooling tube is low, the amount of heat radiation decreases. As a precaution, the amount of heat dissipation is automatically adjusted.

〔Example〕

indicates an intermediate state. In the figure, reference numeral 8 denotes a cooling pipe made of a shape memory alloy, which is formed in a spiral shape. 9 is a heat sink made of aluminum foil stretched between adjacent cooling pipes 80, and 10 is a flexible tube.

FIG. 2 is a sectional view showing the connecting portion between the cooling pipe and the heat sink of the above embodiment. In the same figure (a), 11 is the cooling pipe 8IC.
It is a slit provided. FIG. 2B shows a state in which the heat dissipation plate 9 is inserted into the slit 11 and fixed by being caulked at the caulking portion 12. The figure (e) shows the heat sink 9.
After inserting into the slit 11, the welding part 13 is welded and fixed. Cooling pipe 8 and heat sink 9
may be connected by any method.

When the medium whose temperature rises and is vaporized in the radiator having the structure described above passes through the cooling W8, the heat of the medium is transferred to the heat sink 9 by thermal conduction, and the heat is transferred from the heat sink 9 to space. Dissipates heat by radiation. The larger the surface area of the heat sink, the greater the amount of heat radiation and the greater the cooling capacity.

Since the cooling pipe 8 is made of a shape memory alloy, it contracts as shown in FIG. 1 (IL) below a certain set temperature, and expands as shown in FIG. 1 (e) when the temperature exceeds a certain set temperature.

As an intermediate state, the state in which it is only half-extended is also seen. As the cooling pipe 8 expands and contracts, the heat sink 9
When the radiator is expanded or retracted, its surface area changes and the cooling capacity of the radiator changes accordingly. That is, the cooling pipe 8
When a high temperature medium flows through the cooling pipe 8, it expands and the cooling capacity increases, and when a low temperature medium flows through the cooling pipe 8, it contracts and the cooling capacity decreases. Adjustment of this cooling capacity is performed automatically by simply deforming the shape memory alloy due to heat load, and is extremely simple, without the need for conventional valves or control systems.

FIG. 3 shows a sectional view of a second embodiment of the invention. In the figure, 8 is a cooling pipe formed in a serpentine shape within a plane, 9 is an aluminum foil heat sink stretched between the cooling pipes in the shape of a waterfowl's foot, and 10 is a 7 lexiple tube. It is. The connection between the cooling pipe 8 and the heat sink 9 is the same as in the first embodiment. In the case of this embodiment as well, based on the same principle as the first embodiment, the cooling pipe 8 is adjusted according to the temperature of the medium flowing inside the cooling pipe.
expands and contracts, and accordingly, the heat sink 9 is expanded and retracted, changing its area. Therefore, the operation and effect are the same as in the first embodiment.

In short, the radiator of this embodiment is lightweight, simple, and can automatically adjust the amount of heat radiation by using a cooling pipe made of a shape memory alloy and providing a heat sink made of aluminum foil between them.

〔Effect of the invention〕

The radiator of the present invention includes cooling pipes made of a shape memory alloy formed in a repeating shape such as a spiral or meandering shape, and a heat sink made of aluminum foil stretched between adjacent cooling pipes. Therefore, it is lightweight, simple, and can automatically adjust the amount of heat dissipation.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a sectional view of a first embodiment of a radiator according to the present invention, and (a), (b), and (c) show expansion and contraction states according to various medium temperatures. FIG. 2 is an explanatory diagram of processing the connection portion between the cooling pipe and the heat sink of the above embodiment. FIG. 3 is a sectional view of a second embodiment of the radiator of the present invention.
(a) and (b) are nine expansion/contraction shapes depending on the medium temperature! F! 1 is shown. FIG. 4 is a system diagram of a conventional space station heat exchange system, and FIG. 5 is a system diagram of a conventional heat radiation amount adjustment device. A...Outside the spacecraft, B...Inside the spacecraft,...Evaporator, 2-...Exhaust heat piping,...Radiator,
4...Return pipe,...Pump, 6...Flow rate control valve,...Flow rate control device, 8-...Cooling pipe,...
・・Heat sink, 10−・・Flexible tube, 1
...Slit, 12...Caulking part, 3...Welding part. Agent Patent attorney Akira Saka Seki 1 figure (b) CC) A3rA (α) Kuzu 2 agony (b) CC) (b)

Claims (1)

[Claims] A radiator comprising cooling pipes made of a shape memory alloy formed in a repeating shape such as a spiral or meandering shape, and a heat sink made of aluminum foil stretched between adjacent cooling pipes.