JPH03598A - Three axis attitude control type artificial satellite - Google Patents

Abstract

PURPOSE:To improve the receiving performance characteristic by loading a receiver on a cooling panel as well as mounting optical solar reflectors on the space side of the panel so as to keep the receiver in the low temperature state, thus minimizing the noise factor of the receiver. CONSTITUTION:The title artificial satellite is formed of an earth directing panel 1 with mission machinery and tools on board, a U-shaped cooling panel provided thereon, an insulation for insulating the heat conduction of both panels 1, 16, connecting bolts 17 for connecting the cooling panel 16 to the earth directing panel 1 through the insulation, and optical solar reflectors mounted on the space side of the cooling panel 16. A receiver is disposed on the cooling panel 16 for maintaining the low temperature state by performing heat radiation to the space from the optical solar reflectors 7, thus minimizing the noise factor of the receiver and eventually improving the receiving performance characteristic.

Description

[Detailed Description of the Invention] [Industrial Field of Application] The present invention is to maintain a receiver at a low temperature by placing it on a cooling panel provided in the earth-oriented surface panel, thereby improving the receiving performance index. This is related to a three-axis attitude controlled artificial satellite.

[Conventional technology]

FIG. 8 is an external view of a conventional three-axis attitude control type artificial satellite, and FIG. 9 is a layout diagram of its mission panel.

In the figure, (1) is the earth orientation panel, (2) is the north panel, (31 is the east panel, (4) is the antenna that sends and receives signals to the ground station, and (5) is the solar array paddle. The yoke part mechanically connects the satellite body, (6) is a solar battery paddle that supplies the satellite's required power, (71 is an optical solar reflector that blocks external sunlight input and radiates heat inside the satellite, and (8) is Hinge part that mechanically connects the antenna (4) and the satellite body, (9) is part of the feeder that sends and receives signals to the antenna (4), α・ is the south panel, αD is the part that connects the solar battery paddle (6) to 1 The solar battery paddle drive unit that rotates the per diem one rotation, the solar battery paddle drive electronics that controls the solar battery paddle drive unit +111, αj is a high heat generating device such as a traveling wave tube amplifier or a solid state amplifier, and a4 is an optical solar A heat dissipation area that radiates heat from the reflector (71 to space), a!3 is a receiver that receives uplink signals transmitted from the ground station via the antenna (4) and part of the feeder (9). The three-axis attitude control satellite is configured as described above, with the north panel (
2) The south panel haze is used as a heat dissipation surface, and all the heat generated by the onboard equipment is radiated into space from this surface. Each heat dissipation surface is equipped with an optical solar reflector that has a low solar absorption rate and a high thermal emissivity. (7) was attached to ensure the required heat dissipation area 0. The receiver A9, which is a low heat generating device, and the switches for switching signals are all placed on the earth-oriented surface panel (fl), and the antenna (4) is a part of the feeder that sends and receives signals between them. By arranging the receiver aS in a close position, the power supply system loss was reduced and the required reception performance index was obtained. like.

By arranging the receiver on the earth-oriented surface panel and connecting part of the feeder with a feeding cable or waveguide as short as possible, we can reduce the feeding system loss and obtain the required receiving performance index for the satellite system.・The reception figure of merit is obtained as G/T (geo-overty) by subtracting the logarithmically converted sum of antenna thermal noise, feed system loss, and receiver noise figure from the antenna gain. It is certainly improved by making it smaller. However, there are limits to layout designers in reducing power supply system losses.
In satellite system design, fF requires high tracking accuracy in the user spacecraft acquisition and tracking system, the required receiving performance index is large, and there are many layout design constraints when designing a data relay tracking satellite system. Therefore, a major challenge has been to establish a method for improving the reception performance index when the required reception performance index cannot be obtained.

This invention was made to solve this problem. By implementing a large optical solar reflector to secure a heat dissipation area, keeping the cooling panel and the receiver mounted on the panel at a low temperature, and reducing the noise figure of the receiver, the receiving performance index is improved. The purpose is to obtain a three-axis attitude-controlled artificial satellite that can measure

Moreover, another invention of this invention is in addition to the above-mentioned object.

A cooling panel integrated with a thermocouple plate is installed in the earth-oriented surface panel section, and by passing a stain flow through the thermocouple plate from a power controller, the cooling panel and panel The objective is to obtain a three-axis attitude control artificial satellite that improves the reception performance index by keeping the receiver mounted on the satellite at a low temperature and reducing the noise figure of the receiver.

[Means to solve problems]

The three-axis attitude control artificial satellite according to the present invention includes a U-shaped cooling panel insulated from the satellite body by insulation in the earth-oriented surface panel section.

A receiver is mounted on this cooling panel, and an optical solar reflector is mounted on the outer space side of the panel.

Further, a three-axis attitude control artificial satellite according to another invention of the present invention is provided with a cooling panel insulated from the satellite main body by insulation in the earth-oriented surface panel section, and a receiver is mounted on the cooling panel. It is equipped with a thermocouple plate that is integrated with the panel, and controls this current by passing an ITT current from a power controller through lead wires to the thermocouple plate integrated with the panel.

[Effect]

In this invention, heat is efficiently radiated from the outer space side of the cooling panel, which is thermally insulated between the earth-oriented surface panels by insulation, through the optical solar reflector. kept at a low temperature,
The installed receiver has a small noise figure, and as a result, the receiving figure of merit is improved.

In another invention of the present invention, a lead wire is connected from a power controller to a thermocouple plate which is integrated with a cooling panel which is thermally isolated by insulation between the earth-oriented surface panel and the cooling panel. When a current is passed, an endothermic force based on the Peltier effect is generated, which keeps the cooling panel at a low temperature and reduces the noise figure of the mounted receiver.
As a result, the reception figure of merit is improved.

〔Example〕

FIG. 1 is an external view of a three-axis attitude control type artificial satellite showing one embodiment of the present invention, and FIG. 2 is an external view of a three-axis attitude control type artificial satellite according to another invention of the present invention. FIG. 3 is a layout diagram of a mission panel of a three-axis attitude control type artificial satellite showing an embodiment of the present invention.

FIG. 4 is a layout diagram of a mission panel of a three-axis attitude control artificial satellite according to another invention of the present invention.

FIG. 5 is a cross-sectional view of a three-axis attitude control type artificial satellite showing one embodiment of the present invention, FIG. 6 is a cross-sectional view of a three-axis attitude control type artificial satellite according to another invention of the present invention, and FIG. is a connection diagram of a three-axis attitude control type artificial satellite in another invention of this invention.

In the figure, (1) to α9 are exactly the same as the conventional device described above, the eel is a U-shaped cooling panel, and the wholesaler is a connecting pole connecting the cooling panel and the earth-oriented surface panel).all is the current. Thermocouple plate (1
9 is the cooling panel that is integrated with this thermocouple plate, the can is the heat insulation insulation that insulates between the earth-oriented surface panel and the cooling panel, and the can is the multilayer insulation that measures the mastery of this between the outer space and the panel surface. ration, ■ is a lead wire that supplies current to the thermocouple plate aI.

(to) is a power controller that is a bus device that controls the current flowing to the thermocouple plate 08 via the lead wire @, and @ is a heater that performs temperature compensation for the receiver aS at low temperatures. A three-axis attitude control artificial satellite, which is an embodiment of the present invention, is provided with a U-shaped cooling panel (e) on the earth-oriented surface (1) as shown in FIG. 1, and as shown in the layout diagram in FIG. The receiver a9 is placed on the panel as shown in FIG. Due to system loss, a signal is supplied from part of the feeder (91 to the receiver).The U-shaped cooling panel (1e is a heat insulating material such as glass fiber reinforced plastic, as shown in the cross-sectional view in Figure 5). A small amount of the earth-oriented surface panel (11) is installed in the heat insulation insulation (total) with Earth-oriented surface panel i due to heat conduction between panels
The U-shaped cooling panel (which conducts to the IO through the l+ and prevents the panel temperature from increasing) is placed on the outer space side of the U-shaped cooling panel that is thermally shielded from the satellite body. , an optical solar reflector (]) with low solar absorption and high thermal emissivity is installed, and the non-installed side is covered with multilayer insulation Q9 made of aluminized Kapton, Mylar, etc., and is a heat insulating surface. becomes b
Ru. At this time, the thermal environment of the U-shaped cooling panel αO is balanced by the balance of sunlight irradiation intensity, sun angle, calorific value of mounted equipment, and heat radiation area. Therefore, the U-shaped cooling panel (l
By making the heat dissipation area of e slightly larger than the value based on thermal design, it is possible to place the receiver α in an ideal low-temperature environment where the noise figure is extremely small, and the receiving performance index can be improved. can. Now.

As mentioned above, this invention enables the panel on which the receiver is mounted to be insulated from the satellite body,
By making the heat dissipation area slightly larger than the value based on thermal design, the receiver is placed in a low-temperature environment.
Thermocouple plate on the earth orientation plane +11 as shown in the figure) a
A cooling panel α$ integrated with the receiver a! is provided as shown in the layout diagram of FIG. Place 9 on the panel and b. The cooling panel α9 is installed near the feeder part (9) that supplies the signal from the antenna (4). As shown in the cross-sectional view of FIG.
(1) and become proficient with the earth-oriented surface panel (1).

As a result, a part of the generated heat radiated from the heat radiation area α by the high heat generation device 0 is conducted to the cooling panel (19) via the earth-oriented surface panel (11) due to heat conduction between the panels.
This prevents an increase in panel temperature. This cooling panel (with thermocouple plate αa integrated with I!I) is thermally shielded from the satellite body.

The power controller (c), which is a bus device, is connected through a lead wire port as shown in FIG. 1, and current is caused to flow from the power controller to the thermocouple plate AS in accordance with a command signal from the ground station. When a current is passed through the thermocouple plate ag to which dissimilar metals are joined, an endothermic action based on the Peltier effect occurs on the joint surface. Due to this heat absorption effect, the temperature of the cooling panel α3 is lowered, so that the receiver 19 can be placed in an ideal low-temperature environment where the noise figure is extremely small.

The reception figure of merit can be improved. Refrigerators that utilize the Peltier effect of thermocouples have already been put into practical use, and the thermocouple plate 0a in this case also uses existing technology, and is made of copper-constantan or iron-copper, which has a proven track record for space use.
This can be fully realized using a thermocouple such as constantan. Receiver (temperature compensation on the low temperature side of the US unit is by heater (to)
(0N10FF control).

〔Effect of the invention〕

The present invention is based on the above-described method, by providing a U-shaped cooling panel on the earth-oriented surface panel, which is a mission panel of a satellite, and mounting a receiver thereon.

The receiver can be placed in an ideal low-temperature environment where the noise figure is extremely small. Therefore, it has the effect of improving the reception performance index. Another invention of the present invention is to install a cooling panel integrated with a thermocouple plate on the earth-oriented surface panel and mount the receiver on the earth-oriented surface panel. Can be placed in a low temperature environment. Therefore, it has the effect of improving the reception performance index.

[Brief explanation of drawings]

Fig. 1 is an external view of a three-axis attitude control type artificial satellite showing one embodiment of the present invention, Fig. 2 is an external view of a three-axis attitude control type artificial satellite according to another invention of the present invention, and Fig. 3 4 is a layout diagram of a mission panel of a three-axis attitude control type artificial satellite showing an embodiment of the present invention, and FIG. 4 is a layout diagram of a mission panel of a three-axis attitude control type artificial satellite according to another invention of the present invention)
235 is a sectional view of a three-axis attitude control type artificial satellite showing one embodiment of the present invention, FIG. 6 is a cross-sectional view of a three-axis attitude control type artificial satellite in another invention of this invention, and FIG. The figure is a connection diagram of a three-axis attitude control type artificial satellite in another invention of this invention#
Figure 8 is an external view of a conventional three-axis attitude control satellite;
The figure is a layout diagram of the mission panel of a conventional three-axis attitude control satellite. In the figure, (1) is the earth-oriented panel, (2) is the north panel, and (3) is the east-west panel # (
4) is the antenna, (5) is the yoke part, (61 is the solar array paddle, (7) is the obtical polar reflector, (8) is the solar array paddle, and (8) is the solar array paddle.
) is the hinge part, (9) is part of the feeder, αG is the south panel, αB is the solar array paddle drive unit, and α2 is the solar array paddle drive electronics. αj is high heat generation equipment, α is heat dissipation area, αri is receiver,
ae is a U-shaped cooling panel, αD is a connecting bolt, as
is the thermocouple plate, a9 is the cooling panel, (2Q is the heat insulation insulation, 011 is the multilayer insulation. (to) is the lead wire, @ is the power controller, and 04 is the heater b). Note that the same reference numerals in each figure indicate the same or corresponding parts.

Claims (2)

[Claims] (1) Earth-oriented surface panel carrying mission equipment;
A U-shaped cooling panel provided on this earth-oriented surface panel, an insulator that prevents heat conduction between this cooling panel and the earth-oriented surface panel, and a cooling panel that is cooled through this insulation. The cooling system consists of a connecting bolt that connects the solar panel to the earth-oriented surface panel, and an optical solar reflector mounted on the outer space side of the cooling panel.The cooling system maintains a low temperature by radiating heat from the optical solar reflector to outer space. Place the receiver on the panel for
A three-axis attitude control artificial satellite that improves the reception performance index by reducing the noise figure of the receiver. (2) Earth-oriented surface panel carrying mission equipment;
A cooling panel provided on this earth-oriented surface panel,
A thermocouple plate integrated into the cooling panel, a lead wire for passing current through the thermocouple plate, and a power controller that controls the current flowing through the thermocouple plate via the lead wire according to a command signal from the ground. It consists of an insulation that prevents heat conduction between the cooling panel and the earth-oriented surface panel, and a connecting bolt that connects the cooling panel to the earth-oriented surface panel through this insulation.
The receiver is placed on a cooling panel that is kept at a low temperature by the endothermic action of the thermocouple plate based on the Peltier effect.
A three-axis attitude control artificial satellite that improves the reception performance index by reducing the noise figure of the receiver.