JPH03597A - Three axis attitude control type artificial satellite - Google Patents

Abstract

PURPOSE:To improve the receiving performance characteristic by performing efficient heat radiation to the space from optical solar reflectors and placing a receiver disposed on a cooling panel under the low-temperature environment where a noise factor becomes extremely small. 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, optical solar reflectors 7 mounted on the space side of the cooling panel 16, and micro-heat pipes 18, integrally provided with the cooling panel 16, for performing efficient heat radiation from the reflectors 7. With this structure, the receiving performance characteristic is improved by performing efficient heat radiation to the space from the optical solar reflectors 7 and placing a receiver disposed on the cooling panel 16 under the ideal environment of low temperature where a noise fctor becomes extremely small.

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention is a three-dimensional system that improves reception performance by arranging a receiver on a cooling panel provided on the earth-oriented surface panel and keeping it in a low temperature state. This relates to an axial attitude control type artificial satellite.

[Conventional technology]

FIG. 7 is an external view of a conventional three-axis attitude control type artificial satellite, and FIG. 8 is a layout diagram of its mission equipment panel. In Figure 2, (1) is the earth-oriented surface panel, (2)
is the north panel, (3) is the east panel, (4) is the antenna that sends and receives signals to the ground station, (5) is the yoke that mechanically connects the solar array paddle to the satellite body, and (6) is the satellite. Solar paddles provide the required power.

(7) is an optical solar reflector that blocks external sunlight input and radiates heat inside the satellite, and (8) is an antenna (4).
) and the satellite body, (9) is a part of the feeder that sends and receives signals to the antenna (4), α is the south panel, (lυ is the solar array paddle (6) that is used for daily allowance) 9
The solar array paddle drive unit that rotates one revolution, the solar array paddle drive unit αυ, the heliocentric paddle drive electronics that control the solar array paddle drive unit αυ, the α unit that controls high heat generation equipment such as traveling wave tube amplifiers and solid-state amplifiers, and the α unit that operates the optical solar reflector. (7)
The aS is a receiver that receives uplink signals from the ground station via an antenna (4) and a portion of the feeder (9).

A conventional three-axis attitude control artificial satellite is configured as described above, with the north panel (2) and the south panel (4) used as heat dissipation surfaces in geostationary orbit, and all the heat generated by the onboard equipment is transferred to space from these surfaces. In order to release the heat, an optical solar reflector (7) having a low solar absorption rate and a high heat emissivity was attached to each heat dissipation surface to ensure the required heat dissipation area α4.

9. The receiver αS, which is a low heat generating device, and switches for switching signals are all placed on the earth orientation panel (1). By arranging the receiver αl as close as possible to the feeder part (9) that transmits and receives signals to and from the antenna (4), the feeding system loss can be reduced and the required reception performance index can be obtained.

[Problem to be solved by the invention]

Conventional three-axis attitude control satellites are as described above.

By placing the receiver on the earth-oriented surface panel and connecting it to part of the feeder with a feeder cable or waveguide as short as possible, we can reduce the loss in the feeder system and obtain the required reception performance index for the satellite system. Ta. The reception figure of merit is calculated by subtracting the logarithmically converted sum of the antenna thermal noise, feed system loss, and receiver noise figure from the antenna gain.
This can certainly be improved by reducing the power supply system loss. However, reducing feed system loss has limitations in layout design, and in satellite system design, in particular, it is necessary to obtain high tracking accuracy in the user spacecraft acquisition and tracking system, so the required reception performance index is large. , and in the system design of data relay tracking satellites, which have many layout design constraints, it has become a major challenge to establish a method for improving the reception performance index when the required reception performance index cannot be obtained.

This invention was made in order to solve this problem, and an optical solar panel with low sunlight absorption and high thermal emissivity is installed on the outer space side of the U-shaped cooling panel provided on the earth-oriented surface panel. By mounting a reflector to secure a heat dissipation area and efficiently radiating heat to space using a micro heat pipe integrated with the cooling panel, the receiver mounted on the cooling panel has a noise figure The purpose of this study is to obtain a three-axis attitude control artificial satellite that improves the reception figure of merit under an ideal low-temperature environment where the In addition to the above-mentioned object, another invention of the present invention is provided with a north-south surface connecting heat pipe integrated into a cooling panel provided in the earth-oriented surface panel section, and a north-south surface connecting heat pipe is provided which is a heat dissipation surface of a satellite on a geostationary orbit. Optical solar reflectors with low solar absorption and high thermal emissivity are mounted on the space side of both sides, and efficiently radiate heat, making the receiver mounted on the cooling panel ideal for low noise figures. The purpose is to obtain a three-axis attitude control artificial satellite that improves the reception figure of merit in a low-temperature environment.

[Means to solve the problem]

The three-axis attitude control artificial satellite according to the present invention is equipped with an earth-oriented surface panel, a U-shaped cooling panel thermally isolated by heat insulation, and an integrated micro heat pipe and space The Optical Saw 2 reflector attached to the open side radiates heat efficiently, placing the receiver placed on the cooling panel in an ideal low-temperature environment with an extremely low noise figure.

In addition, a three-axis attitude control artificial satellite according to another invention of the present invention is provided with a cooling panel that is thermally isolated by heat insulation insulation on the earth-oriented surface panel, and has an integrated north-south surface connection. Equipped with a heat pipe, it radiates heat more efficiently than the optical solar reflectors mounted on both the north and south sides of space, and places the receiver placed on the cooling panel in an ideal low-temperature environment with extremely low noise figure. .

[Effect]

In this invention, an optical polari 7 rectifier is mounted on the outer space side of a U-shaped cooling panel provided as a heat shield to the earth-oriented surface panel.

Thermal conduction micro heat pipes radiate heat efficiently, keeping the cooling panel at a low temperature. Therefore, the noise figure of the receiver mounted on the cooling panel becomes extremely small.

In addition, in another invention of the present invention, a cooling nozzle (a cooling nozzle) provided as a heat shield on the earth-oriented surface panel (a north-south connecting heat nozzle (eve) integrally embedded in the flannel) heats the heat on the υ cooling panel. The heat is efficiently dissipated by the optical solar reflectors mounted on both the north and south sides.This lowers the temperature of the receiver mounted on the cooling panel and reduces the noise figure to an extremely low level.

〔Example〕

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. The figure 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 type 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, and FIG. 6 is a cross-sectional view of a three-axis attitude control type artificial satellite according to another invention of the present invention.

In the figure, members (1) to 1 are exactly the same as the above-mentioned conventional device, s, b, (ls is a U-shaped cooling panel, αη is a connecting pole that connects the cooling panel and the earth-oriented surface panel)
, t18 is a micro heat pipe integrated with a U-shaped cooling panel, (1!J is a cooling panel,
00 is a north-south surface connecting heat pipe that is embedded in this cooling panel σ and efficiently conducts heat to each heat radiation area I on the south and north surfaces, Qη is a U-shaped cooling panel aQ and a cooling panel (19, Thermal insulation that thermally isolates between the earth-oriented surface panel (1), and multilayer insulation that thermally isolates between outer space and the panel surface.

(2) is radiant heat radiated from the optical solar reflector (7) to outer space.

As shown in Fig. 1, a three-axis attitude control area artificial satellite, which is an embodiment of the present invention, is equipped with an optical polarity rectifier (7) and a micro heat pipe integrated on the earth-oriented surface panel +1). A U-shaped cooling panel housing e is provided, and a receiver (1!1) shown in the layout diagram of FIG. 3 is arranged on the panel.

The U-shaped cooling panel αe is installed near the feeder part (9) that supplies the signal from the antenna (4), and allows the signal to be sent from the feeder part (9) to the receiver α9 with small power feeding system loss. is supplied. As shown in the cross-sectional view in Figure 5, the U-shaped cooling panel αe is thermally isolated from the earth-oriented surface panel (1) by means of a heat-insulating insulation c1 made of glass fiber-reinforced plastic or the like. has been done. As a result, a part of the heat generated by the high-heating equipment (l) radiates from the heat radiation area a4 is transferred to the U-shaped cooling panel through the earth-oriented surface panel (1) due to heat conduction between the panels. Prevent conduction.On the space side of the U-shaped cooling panel (le), there is an optical solar reflector (7) with low solar absorption and high thermal emissivity.
is attached, and the non-attached surface is covered with multilayer insulation made of aluminized Kapton, My 2, etc., and is thermally isolated from outer space.

The heat generated by tilting the receiver mounted on the U-shaped cooling panel αe is conducted in the form of efficient heat diffusion toward outer space through nine micro heat pipes (1s) embedded integrally with the panel. It is radiated as radiant heat from the optical solar reflector (7) provided on the space side.

In this case, the thermal environment of the receiver αe mounted on the U-shaped cooling panel αe is expressed by the following balanced equation.

A-1! ?・From σT4・η−A・α ' do l
+ Q −−−−・−(1) Here, A: Area of the heat dissipation surface [Z] σ: Stefan Boltmann constant (s, 5yxto vr7zini4) T: Operating average temperature of the micro heat pipe (K) η : Radiation fin efficiency (a, S) Engineering S: Solar irradiation intensity (summer solstice: 1310W/7F+'
, Winter solstice: 1400W/7F? ) θ: Sun angle (2
λ5cleg) q: Amount of heat generated by the receiver [W] α: Solar absorption rate (α25) ε: Thermal emissivity (0,8) F: Shape factor when viewing outer space from the heat radiation surface (1,0) In other words, reception This shows that the environmental temperature at the top of the aircraft is determined by the balance of the large rainfall irradiation intensity, the sun angle, the amount of heat generated by the receiver, and the area of the heat dissipation surface. By making the heat dissipation area of the U-shaped cooling panel (IQ) slightly larger than the thermal design value based on room temperature, the receiver (1!9) can be placed in an ideal low-temperature environment where the noise figure is extremely small. It can be seen that the reception figure of merit can be improved.

Now, as mentioned above, this invention is a receiver a! The panel carrying the 9 is thermally isolated from the satellite main body by the insulation injection 12D, and the heat dissipation area equipped with the optical solar reflector (7) is slightly larger than the thermal design value, and the receiving mtts is placed in a low-temperature environment. As shown below, a three-axis attitude control artificial satellite according to another invention of the present invention has a north-south surface connecting heat pipe (toward) on an earth-oriented surface panel (1) as shown in FIG. A cooling panel +1'J is provided, and a communication receiver a$ shown in the layout diagram of FIG. 4 is arranged on the panel.

The cooling panel <11 is provided near the feeder part (9) that supplies the signal from the antenna (4), and the signal is supplied from the feeder part (9) at the time of the receiver with small power supply system loss. As shown in the cross-sectional view of FIG. 6, the α value of the cooling panel is determined by insulation c11) having heat insulating properties such as glass fiber reinforced plastic.

It is thermally isolated from the earth-oriented surface panel (1). As a result, a part of the amount of heat generated by the high heat generating equipment (13) radiated from the heat radiation area I is conducted to the cooling panel α through the earth-oriented surface panel (1) due to heat conduction between the panels, and This prevents the temperature from rising.

The outer space side of the cooling panel α value is made of multilayer insulation (2
) and is thermally isolated from outer space.

The heat generated by the receiver aS mounted on the cooling panel α-Y is conducted in the form of efficient heat diffusion in each direction to the south and north faces through the north-south face connecting heat pipes that are embedded and integrated with the panel. Then, it is radiated by an optical solar reflector (7) mounted on the outer space side of the heat dissipation area α of each surface. in this case.

The thermal environment in which the receiver α-Hou is placed can be determined by the satellite thermal environment equilibrium equation (1) above, and the environmental temperature in which the receiver is placed is determined by the solar irradiation intensity, the sun angle, and the amount of heat generated by the receiver. This shows that it is determined by the balance of the area of the heat dissipation surface. From this.

By slightly increasing the mounting area of the optical solar reflectors (7) on the south and north sides, which are the heat dissipation area of the cooling panel member that mounts the upper receiver 9, which is a low heat generation device, (based on the thermal design value based on room temperature), It can be seen that the receiver α9 can be placed in an ideal low-temperature environment where the noise figure is extremely small, and the reception figure of merit can be improved.

Regarding the embedding of heat pipes in honeycomb panels, space demonstrations have already been carried out, and the method for connecting heat pipes on both the north and south sides has been improved by applying the conventional in-plane connection method. There is no problem. Note that temperature compensation on the low temperature side of the receiver (IS alone) is performed by ON10 IF? control of the built-in heater.

〔Effect of the invention〕

The present invention is based on the above-described method, by providing a U-shaped cooling panel in which a micro heat pipe is integrated and embedded 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. In addition, another invention of the present invention is to provide a cooling panel in which a north-south surface connecting heat pipe is integrated and embedded on the earth-oriented surface panel, and to mount a receiver thereon, so that the receiver has an extremely low noise figure. It can be placed in an ideal low temperature environment. Therefore, it has the effect of improving the reception performance index.

[Brief explanation of the drawing]

Fig. 1 is an external view of a three-axis attitude control type artificial satellite showing an 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. FIG. 4 is a layout diagram of a mission panel of a three-axis attitude control type artificial satellite showing an embodiment of the invention, 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, and FIG. FIG. 6 is a sectional view of a three-axis attitude controlled artificial satellite according to another embodiment of the present invention, and FIG. 1 is a conventional three-axis attitude controlled artificial satellite. FIG. 8, an external view of a control type artificial satellite, is a layout diagram of a mission panel of a conventional three-axis attitude control type artificial satellite. In the figure, (1) is the earth orientation panel, (2) is the north panel, (3) is the east panel, (4) is the antenna, (
5) is the yoke part, (6) is the solar array paddle, (7) is the optical solar reflector, (8) is the hinge part, (9)
is the feeder section, α is the south panel, and υ is the solar array paddle drive section. (1 is solar array paddle drive electronics, (I3
is a high heat generating device, a4 is a heat dissipation area, α$ is a receiver, αe is a U-shaped cooling panel, is a connecting pole), a8 is a micro heat pipe, (I9 is a cooling panel, and a wire is a north-south connecting heat Pipe, Q is insulation insulation, (
2) Multilayer insulation (c) shows radiant heat. 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 insulation that blocks heat conduction between this cooling panel and the earth-oriented surface panel, and a cooling panel that connects the cooling panel through this insulation. A coupling bolt that connects to the earth-oriented surface panel, an optical solar reflector mounted on the space side of the cooling panel, and an optical solar reflector that is integrated with the cooling panel in order to efficiently radiate heat from this optical solar reflector. Composed of a micro heat pipe, the optical solar reflector efficiently radiates heat into space, and the receiver placed on the cooling panel is placed in an ideal low-temperature environment with an extremely low noise figure, improving reception performance. A three-axis attitude control artificial satellite characterized by improved index. (2) Earth-oriented surface panel carrying mission equipment;
A cooling panel provided on this earth-oriented surface panel,
A north-south connecting heat pipe integrated into this cooling panel, an insulation that blocks heat conduction between the cooling panel and the earth-oriented surface panel, and a cooling panel that connects the cooling panel to the earth-oriented surface panel through this insulation. It consists of a coupling bolt that connects to the spacecraft, and an optical solar reflector mounted on the space side of the south and north surfaces, which are the satellite's heat dissipation surfaces in geostationary orbit.The optical solar reflectors efficiently radiate heat into space and provide cooling. A three-axis attitude control artificial satellite that improves the reception performance index by placing the receiver placed on the satellite panel in an ideal low-temperature environment where the noise figure is extremely low.