JPH1016897A - Temperature control structure of space structure - Google Patents

Abstract

(57) Abstract: Provided is a temperature control structure for a space structure capable of controlling the temperature to a predetermined temperature using radiation absorption and suppressing power consumption related to the temperature control. SOLUTION: A temperature adjusting belt 41 whose radiation absorption rate changes in a longitudinal direction is driven by a driving motor 43 along an outer surface of a directional outer plate 21 of a housing 20 for housing the experimental equipment 30. It is configured.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a temperature control structure for a space structure in which the internal temperature is controlled to a predetermined value by utilizing radiation from a radiation source.

[0002]

2. Description of the Related Art Space structures such as satellites in orbit around the earth receive solar radiation, reflected solar radiation (albead light) from the earth, and terrestrial radiation. Radiates into space. That is, the heat quantity due to radiation such as solar radiation flows in and dissipates the heat quantity from the surface. Therefore, when no temperature control is applied, the input (radiation absorption) and output (radiation) according to the thermo-optical characteristics (characteristics of solar absorptance and infrared emissivity) of the outer surface
Becomes the equilibrium temperature (radiation equilibrium temperature), but the input quantity changes with the change of the angle of the surface receiving the radiation with respect to the sun or the earth as the radiation source, and therefore the equilibrium temperature also changes. still,
When heat is generated from the internal device, the equilibrium temperature including the amount of heat generated by the internal device is included.

[0003] However, various devices provided inside the space structure are required to maintain the temperature within a certain range in order to operate stably. Therefore, the entire outer surface of the structure is covered with a heat insulating material to shut off both input and output of heat to prevent a temperature change caused by them, and to provide a temperature control device capable of heating or cooling, and to provide a predetermined temperature inside the structure. Is maintained by the temperature control device.

[0004]

However, since the power supply is limited in the space structure, there is a demand to minimize the power consumption required for temperature control.

Therefore, it is conceivable to use radiation from the sun or the earth for temperature control by selecting the thermo-optic characteristics of the outer surface without covering the outer surface with a heat insulating material. It is difficult to maintain the desired temperature because the input amount changes with the change of the angle with respect to the source, and it is also necessary to provide a temperature control device capable of heating or cooling and to perform temperature control It is.

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned problems, and has been made in consideration of the above-mentioned problem, and is intended to provide a space structure capable of controlling temperature to a predetermined temperature by using radiation absorption and suppressing power consumption related to temperature control. It is an object to provide a temperature control structure.

[0007]

A space control structure for a space structure which achieves the above object has a radiation absorption coefficient which can change the radiation absorption rate on the outer surface of the space structure which receives radiation from a radiation source. It is characterized in that it is provided with changing means, and the radiation absorption rate changing means is configured to adjust the temperature by changing the radiation absorption rate according to the radiation situation.

The radiation absorptivity changing means includes a temperature control member movably provided on the outer surface and a drive means for moving and driving the temperature control member. It has a larger area in the movement direction than the outer surface and is formed to have a different radiation absorptance depending on the region, and the radiation absorptivity in the entire surface corresponding to the outer surface changes by movement by the driving means. And

Here, to make the radiation absorptivity different depending on the portion of the temperature control member is constituted, for example, by applying a paint color to two colors having different radiation absorptances.

[0010]

Embodiments of the present invention will be described below with reference to the accompanying drawings. FIG. 1 is a perspective view showing a schematic configuration of an orbiting structure around the earth to which an embodiment of a temperature control structure for a space structure according to the present invention is applied.

The illustrated orbiting orbit structure 1 flies in orbit around the earth while maintaining a constant attitude with respect to the earth. A part of the experimental equipment mounting part 1 as shown in a perspective view in FIG.
0 is provided in a state where it is exposed to outer space.

The experimental equipment mounting portion 10 is provided with a plurality of coupling mechanisms 11 on its outer surface. The coupling mechanism 11 has a housing 2 as a space structure in which the experimental equipment is stored.
0 is detachably connected.

As shown in FIG. 3, which is a cross-sectional view taken along the line AA of FIG. 2, the storage housing 20 has a rectangular parallelepiped shape and is disposed inside thereof in parallel with the earth-directed outer panel 21 on the lower side in the figure. Support plate 22
The laboratory equipment 30 is provided supported by.

Between the support plate 22 and the earth-directed outer plate 21,
A heat conductive plate 23 made of a material having a high thermal conductivity such as aluminum is interposed, and heat is transferred from the earth-facing outer plate 21 to the experimental equipment 30 supported by the support plate 22 via the heat conductive plate 23. Communication is to take place.

A temperature control mechanism 40, which is an embodiment of a temperature control structure according to the present invention, is provided around the experimental equipment 30.

Here, the temperature control mechanism 40 of this configuration example is
The earth directing surface, which is the lower surface in the drawing of the housing 20, is used as an incident outer surface, and the radiation incident on the earth directing surface is used for temperature control of the experimental equipment 30. This is because the top and side surfaces receive direct radiation from the sun, but the incident radiation of solar radiation varies greatly due to changes in the relative position to the sun accompanying the flight of the structure 1, and the maximum incident radiation is large,
It is intended to utilize stable reflected solar radiation from the earth and terrestrial radiation for controlling the temperature of the experimental equipment 30 without using radiation having a large absolute amount and a large change. For this reason, the upper surface and the side surface of the storage enclosure 20 in the figure are covered by a heat insulating sheet 24 in which a plurality of layers of resin cloth or the like on which aluminum is deposited are stacked, and the heat insulating sheet 24 absorbs radiation from the surface and externally. To prevent radiation.

The temperature control mechanism 40 is configured such that a temperature control belt 42 as a temperature control member is wrapped around support rollers 41 disposed inside the four corners of the storage case 20 so that the storage case 20
The temperature control belt 42 is rotated by a drive motor 43 provided on the support plate 22, and is rotated by one of the lower support rollers 41A in the figure. It is configured to be driven.

The drive motor 43 is driven and controlled by a control device 50 to which temperature information from the temperature sensor 31 provided in the experimental equipment 30 is input.

A pair of support rollers 41B, C on the upper side in FIG.
Is disposed inside the housing 20, and a pair of lower support rollers 41A and 41D are disposed such that their peripheral surfaces coincide with the outer surface of the earth-directed outer plate 21. As a result, the orbit of the temperature control belt 42 passes through the inside of the housing 20 on the upper side and the side in the figure, and moves on the lower side in the figure by contacting the outside of the earth-directed outer plate 21 with the earth-directed outer plate 21. It is set as follows.

The temperature control belt 42 corresponds to the housing 20 in which a strip-shaped metal plate (unit plate 42A) of aluminum or the like is connected in a so-called caterpillar shape so as to be bent as shown in FIG. It is an endless belt with a width, the outer surface of which is configured to have a different radiation absorptance in the circumferential direction.

FIG. 4 shows a configuration in which the radiation absorptivity differs in the circumferential direction.
As shown in FIG. 7, each unit plate 42A forming the temperature control belt 42 is painted in two colors, black and white, and the proportion of the painted area is gradually different for each adjacent one. A state in which only the white-painted portion corresponds to the earth-directed outer panel 21 of the housing 20 and a state in which only the black-painted portion corresponds to the earth-directed outer panel 21, and the intermediate portion between the two are defined as the earth-directed outer panel. By adjusting the position in accordance with 21, the occupied area ratio between the white painted portion and the black painted portion can be adjusted.

For example, a white paint has a solar absorptivity: αs =
0.15, the black paint has a solar absorptivity: αs = 0.95, and the area ratio between the two is halved when the middle position between the two coincides with the center of the earth-directed outer panel 21 as shown in the figure. Solar absorption rate: α
s is 0.55, and the intermediate position is adjusted to the left and right to change the occupied area ratio between the white paint and the black paint, so that the average solar absorptance: αs of the entire earth-directional surface is 0.15 to
It can be set arbitrarily between 0.95. The divided shape of the white painted portion and the black painted portion may be configured such that the entire periphery is divided into two regions of the white painted portion and the black painted portion as shown in a development view in FIG.

The temperature control belt 42 having the above-described configuration can arbitrarily set the radiant absorptance of the entire earth-facing surface of the storage enclosure 20 by moving the temperature control belt 42 around, thereby adjusting the amount of radiant absorption heat. You can do it.

In the temperature control mechanism 40 configured as described above, the control device 50 controls and drives the drive motor 43 based on the temperature information detected by the temperature sensor 31 provided in the experimental equipment 30. Temperature control belt 42
Is rotated to change the average radiation absorption rate of the entire earth-facing surface of the storage enclosure 20, and adjust the radiation absorption heat quantity to adjust the temperature of the experimental equipment 30. That is, when the temperature of the experimental equipment 30 detected by the temperature sensor 31 is lower than the target temperature, the temperature control belt 42 is moved around in the direction in which the radiation absorptivity increases (+ direction in FIG. 4), and the temperature is higher than the target temperature. In this case, the temperature control belt 42 is moved around in the direction in which the radiation absorptance decreases (the direction in FIG. 4). Accordingly, when the temperature is lower than the target temperature, the radiation absorption heat increases and the temperature rises. When the temperature is higher than the target temperature, the radiation absorption heat decreases, and the target temperature can be maintained. is there.

As a result, only electric power is consumed when the temperature control belt 42 is moved by the drive motor 43, so that the temperature control is always performed by a temperature control device such as a device having a temperature control device capable of heating or cooling. The power consumption can be suppressed without consuming power.

In the above configuration example, the temperature control belt 42 is movably provided here with the earth-directing surface of the structure on the orbit around the earth as the incident outer surface, but the present invention is not limited to this. It may be applied to structures in orbit around other planets, structures revolving around the sun, and structures operating in other orbits. If the posture does not change the positional relationship between the object and the incident outer surface, stable temperature control can be performed.

Further, the configuration in which the temperature control belt 42 is driven to rotate by an endless belt has been described. However, the present invention is not limited to this.

[0028]

As described above, according to the temperature control structure for a space structure according to the present invention, the radiation absorption rate changing means capable of changing the radiation absorption rate is provided on the outer surface of the incidence receiving the radiation from the radiation source. Since the radiation absorptivity changing means is configured to change the radiation absorptance in accordance with the radiation condition, the temperature can be adjusted using the radiation absorption, and the temperature can be controlled by heating or cooling. It is not necessary to provide a device and perform temperature control, and power consumption related to temperature control can be suppressed and rational temperature control can be performed.

[Brief description of the drawings]

FIG. 1 is a perspective view showing a schematic configuration of an orbiting structure around the earth to which an embodiment of a temperature control structure for a space structure according to the present invention is applied.

FIG. 2 is a perspective view of the experimental equipment mounting section.

FIG. 3 is a sectional view taken along line AA of FIG. 2;

FIG. 4 is a development view of a temperature control belt.

FIG. 5 is a development view of another example of the temperature control belt.

[Explanation of symbols]

 Reference Signs List 20 housing housing (space structure) 21 earth-facing outer surface 40 temperature control mechanism (radiation absorptivity changing means) 42 temperature control belt (temperature control member) 43 drive motor (drive means)

Claims (4)

[Claims] An outer space structure receiving radiation from a radiation source is provided with radiation absorption rate changing means capable of changing the radiation absorption rate, and the radiation absorption rate changing means is adapted to absorb radiation according to radiation conditions. A temperature control structure for a space structure, wherein the temperature is controlled by changing a rate. 2. The radiation absorptivity changing means includes a temperature control member movably provided on the outer surface, and a driving means for moving and driving the temperature control member. It has a larger area in the movement direction than the outer surface and is formed to have a different radiation absorptance depending on the region, and the radiation absorptivity in the entire surface corresponding to the outer surface changes by movement by the driving means. The temperature control structure for a space structure according to claim 1. 3. The space structure according to claim 2, wherein the temperature control member is formed in the form of an endless belt, and is disposed so as to move around by the driving means. Temperature control structure. 4. The method according to claim 1, wherein the outer space structure is in orbit around the earth, the radiation source is the earth, and the outer surface is an earth-oriented surface. Temperature control structure for space structures.