JP2003276697A - Artificial satellite - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an artificial satellite which can efficiently fold and accommodate an antenna reflector in a space between a satellite body and an inner circumferential surface of a rocket fairing by using four sides, i.e., east, west, north and south sides of a satellite structure, and mount a large number of large antenna reflectors. <P>SOLUTION: The antenna reflector 13 is folded and mounted at least one of the east and west sides, and the north and south sides of the satellite structure 12, and the artificial satellite 11 in this condition is inserted and accommodated in the rocket fairing 17 so that a back wall surface 13a of each antenna reflector 13 is substantially parallel to the inner circumferential surface of the rocket fairing 17 with a space therebetween when viewed from an earth- directing surface 12a side of the satellite structure 12. <P>COPYRIGHT: (C)2004,JPO

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an artificial satellite equipped with a plurality of large antenna reflectors.

[0002]

2. Description of the Related Art An artificial satellite that can be launched into a satellite orbit by being stored in a rocket fairing is required to be equipped with a large number of devices, so it is important to increase the storage efficiency in the rocket fairing as much as possible. Is. Above all, it is required to mount a large number of large antenna reflectors as satellites become more sophisticated, so how to store the antenna reflectors in the rocket fairing is an important issue in satellite design. .

FIG. 8 shows, for example, US Pat. No. 5,833,17.
FIG. 9 is a perspective view showing a conventional artificial satellite described in No. 5, and FIG. 9 is a plan view of the artificial satellite shown in FIG. 8 housed in a rocket fairing. In the figure, 1 is an artificial satellite, 2 is a satellite structure that is the body of the artificial satellite 1, and this satellite structure 2 is a rectangular parallelepiped having azimuth planes in the north, south, east, and west directions (hereinafter, symmetry planes are referred to as east-west and north-south planes) ing. Reference numeral 3 denotes two large antenna reflectors held (mounted) on the east and west E and W sides of the satellite structure 2 via a folding / expanding mechanism 4.
a is the back wall surface of each antenna reflector 3, 5 is the satellite structure 2
A solar cell paddle held on the N and S sides of the north and south surfaces of the satellite via a folding / expanding mechanism 6, and a cylindrical rocket fairing 7 for storing the artificial satellite 1 at the time of launch.

Here, the satellite structure 2 is constructed such that the width dimension b of the east-west surfaces E and W is larger than the width dimension a of the north-south surfaces N and S. The back wall surface 3 a of each antenna reflector 3 is formed in a spherical shape having a larger radius of curvature than the inner peripheral surface of the rocket fairing 7.

That is, in the above-mentioned conventional artificial satellite, in order to mount the large antenna reflector 3 on the satellite structure 2 by folding, the east-west which becomes the folding mounting surface of the antenna reflector 3 on the four faces of north, south, east and west of the satellite structure 2. The area of the surface is made larger than the area of the north-south surface which is the folding mounting surface of the solar cell paddle 5. Therefore, compared to the east-west surface of the satellite structure 2, the solar paddle 5
It was designed to be folded and mounted only.

Next, the operation will be described. When launching the artificial satellite, the antenna reflectors 3 are folded on both the east and west sides of the satellite structure 2, and the solar cell paddles 5 are folded on the north and south sides of the satellite structure 2, respectively. The satellite structure 2 in this state is the rocket fairing. It is inserted and stored in 7. Since the dimension b on each of the east and west sides of the satellite structure 2 is larger than the dimension a on each of the north and south sides, the east and west sides of the satellite structure 2 housed in the rocket fairing 7 and the rocket fairing 7 are accommodated. A large space is formed between the inner peripheral surface and the inner peripheral surface. Therefore, by utilizing the space, the large antenna reflectors 3 folded and mounted on the east and west sides of the satellite structure 2 can be housed in the rocket fairing 7.

[0007]

Since the conventional artificial satellite is constructed as described above, it is possible to fold and mount a plurality of large antenna reflectors 3 on both the east and west sides of the satellite structure 2. However, with the increase in size of the antenna reflector 3, both the north and south sides of the satellite structure 2 have to be made smaller, and the north and south sides are used as folding mounting surfaces for the solar cell paddles 5 and inside the satellite structure 2. Since it also serves as a surface for exerting a radiator function for releasing generated heat to outer space, and also as a surface for mounting electronic equipment such as communication equipment, when the north and south surfaces of the satellite structure 2 become smaller, the satellite structure becomes smaller. There is a problem that the number of electronic devices to be mounted is limited, and as a result, the communication capacity of the artificial satellite becomes small. Further, since the back wall surface 3a of the antenna reflector 3 having a large size is formed into a spherical shape having a radius of curvature larger than the inner diameter of the rocket fairing 7, the antenna reflector 3 is folded and mounted on both the east and west sides of the satellite structure 2. Then, when stored in the rocket fairing 7, a large dead space is generated between the back wall surface 3a of the antenna reflector 3 and the inner peripheral surface of the rocket fairing 7,
For this reason, the utilization efficiency of the internal space of the rocket fairing 7 is reduced, and the size of the satellite structure 2 must be reduced accordingly, and there is a problem that the number of satellite devices to be mounted is limited.

The present invention has been made to solve the above problems, and an antenna reflector is folded and mounted on at least one of the east and west sides and the north and south sides of a satellite structure, and the antenna reflector is mounted inside a rocket fairing. When stored,
An artificial satellite that can increase the utilization efficiency of the internal space of the rocket fairing so that no dead space is generated inside the rocket fairing, and can increase the satellite structure and increase the number of equipment installed The purpose is to get.

Another object of the present invention is to obtain an artificial satellite which can have a shape configuration of an antenna reflector which can improve the utilization efficiency of the internal space of a rocket fairing.

Furthermore, the present invention is applicable to the entire satellite structure.
The purpose is to obtain an artificial satellite capable of mounting a large number of antenna reflectors of one or more.

A further object of the present invention is to obtain an artificial satellite in which the communication system such as the antenna reflector and the radio wave radiator mounted on the satellite structure can be easily designed.

A further object of the present invention is to obtain an artificial satellite which can increase the heat dissipation capability of the satellite structure and can be equipped with a large number of heat generating devices.

[0013]

In the artificial satellite according to the present invention, an antenna reflector is folded and mounted on both the east and west sides of a satellite structure having four planes of north, south, east, west, and at least one of the north and south sides of the satellite structure. When the antenna reflectors are mounted on the satellite in a folded manner, and the antenna reflectors folded in the satellite structure are viewed from the earth-orientation plane of the satellite structure, their back wall surfaces leave a gap in the inner peripheral surface of the rocket fairing. It is configured to be parallel.

In the artificial satellite according to the present invention, the back wall surface of the antenna reflector is formed into a spherical shape having a radius of curvature substantially the same as the inner diameter of the rocket fairing.

In the artificial satellite according to the present invention, a plurality of antenna reflectors are foldably mounted on at least one of the north, south, east and west sides of the satellite structure.

In the artificial satellite according to the present invention, the distance from the earth-oriented surface of the satellite structure to the folding / unfolding mechanism of each antenna reflector is set to be constant.

In the artificial satellite according to the present invention, the east-west surface of the satellite structure is formed wider than the north-south surface.

[0018]

BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of the present invention will be described below. Embodiment 1. 1 is a schematic perspective view showing an artificial satellite according to Embodiment 1 of the present invention, and FIG. 2 is a plan view of the artificial satellite of FIG. 1 housed in a rocket fairing. In the figure, 11 is an artificial satellite and 12 is an artificial satellite 11.
It is a satellite structure that will be the body of. The satellite structure 12 is a rectangular parallelepiped having four azimuth planes (north, east, west, and north-south planes) in the north, south, east, and west directions, and one end face in the longitudinal direction is an earth-oriented plane 12a.

Reference numeral 13 denotes four large antenna reflectors each of which is folded and mounted one on each of the four north, south, east, and west faces of the satellite structure 12, and these antenna reflectors 13 are provided.
Is held (mounted) on the satellite structure 12 via a folding / expanding mechanism 14. 13a is each antenna reflector 1
3 is a back wall surface, 15 is a solar battery paddle that is folded and mounted on the north and south sides N and S sides of the satellite structure 12 through a folding / expanding mechanism (not shown), and 17 stores the artificial satellite 11 at the time of launch. It is a cylindrical rocket fairing.

Here, each antenna reflector 13 is designed to be folded in a direction in which its respective radio wave radiation surfaces face the north, south, east, and west planes of the satellite structure 12, that is, inward. When viewed from one end surface of the structure 12 (for example, the earth-orientation surface 12a), the back wall surface 13a of each antenna reflector 13 is formed in a spherical shape having a radius of curvature substantially the same as the inner diameter of the rocket fairing 17, as shown in FIG. Has been done.

That is, the antenna reflectors 13 are folded on both the east and west sides of the satellite structure 12 and the satellite structure 1 is
The solar cell paddle 15 is folded on both north and south sides of 2, and the artificial satellite with the antenna reflector 13 folded on the outside of the folded solar cell paddle 15 is inserted and housed in the rocket fairing 17, and the artificial satellite in this state is inserted into the satellite. When viewed from the earth-oriented surface 12a side of the structure 12, as shown in FIG. 2, each back wall surface 13a of each antenna reflector 13 is an arcuate curved surface having the same radius of curvature, and these back wall surfaces 13a are rocket fairings 17. The artificial satellite 11 is configured so as to be parallel to the inner peripheral surface with a slit.

Next, the operation will be described. Artificial satellite 11
In launching the satellite, as described above, the antenna reflectors 13 are provided on both the east and west sides of the satellite structure 12 and the satellite structure 1
The solar cell paddle 15 and the antenna reflector 13 are sequentially folded on both the north and south sides of 2, and the artificial satellite 11 in this state is inserted and housed in the rocket fairing 17. Then, in the artificial satellite 11 launched from within the rocket fairing 17, each antenna reflector 13 and solar cell paddle 15 are deployed in orbit as shown in FIG.

According to the first embodiment described above, the antenna reflectors 13 are folded and mounted on the east and west sides of the satellite structure 12 one by one, and the solar cell paddles 15 are folded on the north and south sides of the satellite structure 12. After mounting, the antenna reflectors 13 are folded and mounted one by one on the outside of the solar cell paddle 15, and the artificial satellite 11 in this state is inserted and housed in the rocket fairing 17 and the earth-oriented surface 12a of the satellite structure 12 is mounted. When viewed from the side, since the back wall surface 13a of each antenna reflector 13 is configured to be substantially parallel to the inner peripheral surface of the rocket fairing 17 with a gap, the rocket fairing 17 accommodating the artificial satellite 11 is formed. There is no useless dead space inside, and the utilization efficiency of the internal space of the rocket fairing 17 is improved. For this reason, the satellite structure 12 can be enlarged without changing the size of the rocket fairing 17, and the antenna reflectors 13 to be folded and mounted on the satellite structure 12 can be increased in size and the number of the antenna reflectors 13 can be increased. This has the effect of increasing the number of devices equipped with.

The artificial satellite 11 is accommodated by forming the back wall surface 13a of each antenna reflector 13 into a spherical shape having a diameter slightly smaller than the inner diameter of the rocket fairing 17 and the same radius of curvature as the inner diameter. There is an effect that wasteful dead space in the rocket fairing 17 can be eliminated to improve the utilization efficiency of the internal space of the rocket fairing 17, and the satellite structure 12 can be enlarged.

Embodiment 2. 4 is a perspective view showing an artificial satellite according to a second embodiment of the present invention, and FIG. 5 is a plan view of the artificial satellite shown in FIG. 4 housed in a rocket fairing. Are denoted by the same reference numerals and redundant description will be omitted. In the first embodiment, the satellite structure 1
Two antenna reflectors 13 are mounted on each of the north, south, east, and west sides, but in the second embodiment, two antenna reflectors 13 are mounted on each of the north, south, east, and west sides of the satellite structure 12.
It is equipped with 18 so that it can be folded and expanded. 1
Reference numeral 8a is a back wall surface of each antenna reflector 18, and 19 is a folding / unfolding mechanism that holds each antenna reflector 18 in the satellite structure 12.

According to the second embodiment described above, two antenna reflectors 13 and 18 are mounted on each of the north, south, east, and west sides of the satellite structure 12 so that they can be folded and deployed. 8 antenna reflectors 1 in 12
There is an effect that 3,18 can be mounted.

Embodiment 3. 6 is a side view showing an artificial satellite according to a third embodiment of the present invention. In the third embodiment, the artificial satellite 11 having the configuration according to the first embodiment is used.
In the above, all of the folding / expanding mechanisms 14 for holding the respective antenna reflectors 13 on the satellite structure 12 are provided at the same distance from the earth-oriented surface 12a of the satellite structure 12.

According to the artificial satellite 11 of the third embodiment having such a configuration, the distance between the radio wave radiator (not shown) attached to the earth-oriented surface 12a of the satellite structure 12 and each antenna reflector 13 is the same. Therefore, the communication system including the antenna reflector 13 and the radio wave radiator can be easily designed.

Fourth Embodiment FIG. 7 is a plan view showing a state in which an artificial satellite according to Embodiment 4 of the present invention is housed in a rocket fairing. In the fourth embodiment, the width dimension a of the east-west surface is set to be larger than the width dimension b of the north-south surface on the four north, south, east, and west sides of the satellite structure 12.

According to the fourth embodiment having such a configuration,
In a three-axis attitude-controlled satellite in a geostationary orbit, the area of the north and south surfaces that function as a radiator that radiates heat from the satellite structure 12 to outer space increases, so the heat dissipation capacity of the satellite structure 12 increases and the equipment mounting area also increases. Therefore, there is an effect that a large number of heat generating devices can be mounted.

Embodiment 5. In the first embodiment, one antenna reflector 13 is foldably and unfoldably mounted on each of the north, south, east, and west sides of the satellite structure 12, but one antenna reflector 13 is mounted on each of the east and west sides of the satellite structure 12. The antenna reflector 13 may be mounted, and one antenna reflector 13 may be mounted on only one of the north and south sides. Even in this case, the same effect as in the first embodiment can be obtained. To be

Sixth Embodiment In the second embodiment, the antenna reflector 1 is provided on each of the north, south, east, and west sides of the satellite structure 12.
It is configured to mount two antennas 3 and 18, but one antenna reflector 13 is mounted on each of the north, south, east, and west sides of the satellite structure 12, and in addition to the north, south, east, and west of the satellite structure 12. For example, one antenna reflector 18 may be mounted on at least one surface. In short, at least one antenna reflector 13 may be mounted on each of the north, south, east, and west sides of the satellite structure 12, and even in this case, the satellite structure 12 has a total of five or more antenna reflectors 13. Antenna reflectors 13 and 1
There is an effect that 8 can be mounted.

[0033]

As described above, according to the present invention, the antenna reflectors are folded and mounted on at least one of the east and west sides and the north and south sides of the satellite structure, and the artificial satellite in this state is mounted in the rocket fairing. When inserted and stowed and viewed from the earth-orientation side of the satellite structure, the back wall of each antenna reflector was configured to be approximately parallel to the inner peripheral surface of the rocket fairing with a gap, so the satellite can be stowed. There is no useless dead space inside the rocket fairing, and the space inside the rocket fairing is used more efficiently. Therefore, the satellite structure can be enlarged without changing the size of the rocket fairing. It is possible to increase the size and increase the number of antenna reflectors to be folded and mounted on the satellite structure.
The effect is that the number of other devices installed can be increased.

According to the present invention, the back wall surface of each antenna reflector is formed into a spherical shape having a diameter slightly smaller than the inner diameter of the rocket fairing and the same radius of curvature as that of the inner diameter of the rocket fairing. There is an effect that the dead space in the fairing can be eliminated to improve the utilization efficiency of the internal space of the rocket fairing and the satellite structure can be enlarged.

According to the present invention, a plurality of antenna reflectors are mounted on at least one of the north, south, east, and west sides of the satellite structure so that they can be folded and stored. There is an effect that can be mounted.

According to the present invention, since all the folding / unfolding mechanisms for holding the respective antenna reflectors are arranged at the same distance from the earth-orientation plane of the satellite structure, the radio wave radiation attached to the earth-orientation surface of the satellite structure is provided. The distance between the antenna and each antenna reflector can be made the same, which facilitates the design of the communication system including the antenna reflector and the radio wave radiator.

According to this invention, since the east-west surface of the satellite structure is formed wider than the north-south surface, the area of the north-south surface of the satellite structure that functions as a radiator for radiating heat from the satellite structure to outer space is large. As a result, the heat dissipation capacity of the satellite structure is increased, and the device mounting area is also increased, so that a large number of heat generating devices can be mounted.

[Brief description of drawings]

FIG. 1 is a schematic perspective view showing an artificial satellite according to a first embodiment of the present invention.

FIG. 2 is a plan view of the artificial satellite of FIG. 1 housed in a rocket fairing.

FIG. 3 is a development view of FIG. 1.

FIG. 4 is a perspective view showing an artificial satellite according to a second embodiment of the present invention.

5 is a plan view of the artificial satellite of FIG. 4 housed in a rocket fairing. FIG.

FIG. 6 is a side view showing an artificial satellite according to a third embodiment of the present invention.

FIG. 7 is a plan view showing a state in which an artificial satellite according to a fourth embodiment of the present invention is housed in a rocket fairing.

FIG. 8 is a perspective view showing a conventional artificial satellite.

9 is a plan view of the artificial satellite of FIG. 8 housed in a rocket fairing. FIG.

[Explanation of symbols]

11 artificial satellites, 12 satellite structure, 12a earth-orientation plane, 13 antenna reflector, 13a back wall surface, 14
Folding and unfolding mechanism, 15 solar array paddle, 17 rocket fairing, 18 antenna reflector, 18a
Back wall, 19 folding and unfolding mechanism.

Claims (5)

[Claims] 1. A satellite structure having four planes of north, south, east, and west, and an antenna reflector mounted on the satellite structure via a folding / expanding mechanism, housed in a cylindrical rocket fairing, and launched. In an artificial satellite, antenna reflectors are folded and mounted on both east and west sides of the satellite structure, and antenna reflectors are folded and mounted on at least one of the north and south sides of the satellite structure, and the antenna reflectors are folded on the satellite structure. When viewed from the earth-oriented surface of the satellite structure, the back wall surface of the satellite structure is configured to be substantially parallel to the inner peripheral surface of the rocket fairing with a gap. 2. The artificial satellite according to claim 1, wherein the back wall surface of the antenna reflector is formed into a spherical surface having a radius of curvature substantially the same as the inner diameter of the rocket fairing. 3. The artificial satellite according to claim 1, wherein a plurality of antenna reflectors are mounted in a foldable manner on at least one of north, south, east, and west faces of the satellite structure. 4. The artificial satellite according to claim 1, wherein the distance from the earth-orientation plane of the satellite structure to the folding / unfolding mechanism of each antenna reflector is set to be constant. 5. The satellite structure according to claim 1, wherein the east-west surface is formed wider than the north-south surface.
The described satellite.