JPH0858700A - Spacecraft - Google Patents

Abstract

(57) [Summary] [Purpose] The satellite is protected by a fairing during launch. In the past, this fairing was separated by decapitation after launching the satellite out of the atmosphere. In the present invention, the fairing is used as a component of the satellite to effectively utilize the launchable weight of the rocket. [Structure] A satellite in which the antennas 4a and 4b are mounted on a fairing 2 and the fairing 2 and the satellite body 3 are integrated. The mount on the inner surface of the fairing 2 may be a sensor or a solar battery cell in addition to the antenna.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an artificial satellite or other spacecraft that is transported from the ground to outer space by a rocket, and more particularly to a spacecraft that uses a fairing as a structure.

[0002]

2. Description of the Related Art A conventional fairing is disclosed, for example, in Japanese Patent Laid-Open No.
-237300, it forms part of a rocket and was used only for the purpose of protecting the satellite from the aerodynamic environment of the atmosphere until it was put into orbit. Therefore, the fairing was separated from the rocket after it passed through the atmospheric environment and before the satellite was separated from the rocket. The fairing then fell to the ground under the influence of gravity.

[0003]

As mentioned above, in the past, the fairing was treated as part of a rocket and was only useful while the satellite was being transported into the atmospheric environment.

Generally, the launchable weight of a rocket is limited, and great efforts are made to keep the weight of a spacecraft such as a satellite within the launchable weight of a rocket. Therefore, the fairing, which is used only during the transportation of the atmospheric environment and is discarded thereafter, has been a serious limiting factor in increasing the launchable weight of the rocket.

The present invention makes effective use of fairings,
As a result, the purpose is to effectively utilize the launchable weight of the rocket.

FIG. 3 is a conceptual diagram showing the relationship between a rocket, a fairing and a satellite in the process of launching a conventional artificial satellite from the ground to an orbit around the earth. In the figure, 1 is a rocket body, 2 is a fairing, 12a, 1
2b is a member forming the fairing 2, 3 is a satellite body,
Parabolic antenna members 14a and 14b are provided. 3 (a) is a front view showing the rocket 1 waiting for launch on the ground, and FIG. 3 (b) is a fairing 2 and the upper part of the outer shell of the rocket 1 are cut away to show the fairing 2 and the upper part of the rocket 1. 3 (c) is a conceptual front view of the interior of the fairing, in which FIG.
a and 2b, and these fairing members 2a,
2b is a front view conceptually showing a state of separating the rocket 1 from the rocket 1, 3 (d) is a conceptual diagram showing a state of separating the satellite body 3 from the rocket body 1, and FIG. 3 (e) is a parabolic antenna member. It is a conceptual diagram which shows the satellite which orbits the earth by expanding 14a and 14b.

[0007]

In order to solve the above-mentioned problems, the present invention provides the following means.

In a spacecraft such as an artificial satellite or the like, which is mounted on the tip of a rocket, is transported from the ground to outer space by the thrust of the rocket, and is separated from the rocket in the outer space to travel in outer space. A spacecraft that is provided with a fairing that shields the main body from the atmosphere and protects the main body from the atmosphere when being transported in the atmosphere.

[0009] A deployment mechanism is provided for joining the fairing and the body and for deploying the fairing in two or more parts after being separated from the rocket. The described spacecraft.

The spacecraft according to the above, wherein at least one antenna is attached to the fairing.

A plurality of the antennas are provided to form the fairing, and among the plurality of fairing members that are separated from each other when the fairing is expanded by the expanding mechanism, the plurality of respective antennas are respectively provided on different fairing members. The spacecraft according to the above, which is attached.

The spacecraft according to the above, wherein the antenna is a parabolic antenna.

The spacecraft according to the above, wherein a plurality of solar cells are attached to the fairing.

The spacecraft according to the above, wherein a sensor is attached to the fairing.

[0015]

In the present invention, as described above, the spacecraft itself has the fairing. When the spacecraft is provided with a fairing, when the spacecraft is separated from the rocket, the fairing is separated from the rocket together with the body of the spacecraft, and the spacecraft is one of the structural members of the spacecraft. Used in.

For example, by connecting the spacecraft body and the fairing in a deployable structure and maintaining the fairing in a shape extending in all directions from the spacecraft in space, the fairing is used as a support structure member for the antenna. it can.

[0017]

EXAMPLES The present invention will be described in more detail with reference to examples.

FIG. 1 is a diagram showing an embodiment of the present invention during navigation in outer space. In FIG. 1 (a), a fairing is divided into four members, and the four members are expanded in four directions. A plan view showing the state, and FIG. 6B is a front view in that state. However, in FIG. 1B, the four-division fairing 2b is omitted. 2A and 2B are views showing the satellite of the embodiment mounted on the rocket 1, where FIG. 2A is a plan view and FIG. 2B is a front view. However,
In FIG. 2B, the front side of the fairing 2 is cut away so that the internal structure of the fairing 2 appears.

The fairing 2 is a combination of four-divided fairing members 2a, 2b, 2c and 2d, and is connected to the satellite body 3 in a developed structure (not shown in the drawing). The fairing 2 is a part of the structural member of the satellite. While the satellite body 3 is mounted on the rocket 1, the four-division fairings 2a, 2b, 2c and 2d
Are combined to form a space for accommodating the satellite body 3 inside, and protect the satellite body 3 from the atmospheric environment. In this respect, the function of the fairing 2 is the same as that of the conventional one shown in FIG. However, in the satellite of this embodiment, the satellite body 3
1 is separated from the rocket body 1, the fairing 2 is not separated, and is still connected to the satellite body 3 through the deployable structure. After the satellite orbits the earth, FIG. ), (B), it is divided into four members and expanded in all directions. Then, these four members, that is, the four-division fairing members 2a, 2b, 2c, 2
Antennas 4a and 4b are attached to 2a and 2c of d, respectively. 4-part fairing member 2
a and 2c act as a support structure for the antennas 4a and 4b.

In the above embodiment, the fairing 2 acts as an antenna support structure. Therefore, after using the fairing 2 as shown in FIG. 3 merely to protect the satellite body 3 from the atmospheric environment, it is thrown out into a space and a special support structure for the antennas 4a and 4b is additionally provided. In comparison, by adopting the satellite structure of this embodiment,
The weight that can be carried to outer space by the rocket 1 can be significantly increased. As described above, in the present embodiment, the fairing 2 is effectively used and the launchable weight of the rocket 1 is effectively used. Therefore, for example, the satellite body 3 having a heavier weight than before can be mounted.

Although the antenna is mounted on the fairing in the above embodiment, various sensors and solar cells can be mounted on the fairing. By mounting the solar cells, the fairing will also be used as a solar paddle.

[0022]

As described above in detail with reference to the embodiments, the present invention effectively increases the launch weight by effectively utilizing the fairing, which was conventionally used only at the time of launch, as a structural member of the satellite. It becomes possible to do.
As a result, the mission weight can be increased, a large amount of propellant can be loaded, and the satellite life can be extended.

[Brief description of drawings]

FIG. 1 is a view showing a satellite according to an embodiment of the present invention in a state where a fairing is deployed while it is navigating in outer space.

FIG. 2 is a diagram showing the embodiment in FIG. 1 in a state in which it is mounted on a rocket.

[Fig. 3] Rocket in the process of launching a conventional satellite from the ground by rocket to the space, fairing,
The conceptual diagram which shows the relationship with a satellite.

[Explanation of symbols]

 1 rocket 2 fairings 2a, 2b, 2c, 2d 4 split fairing members 3 satellite bodies 4a, 4b antennas 12a, 12b 2 split fairing members 14a, 14b parabolic antenna members

Claims (7)

[Claims] 1. A satellite or other spacecraft that is mounted on the tip of a rocket and is transported from the ground to outer space by the thrust of the rocket and is separated from the rocket in the outer space to navigate in outer space. A spacecraft comprising a fairing that shields a main body from the atmosphere and protects the main body from the atmosphere while being transported in the atmosphere by the rocket. 2. The fairing and the main body are connected to each other,
2 after the fairing is cut off from the rocket
The spacecraft according to claim 1, further comprising a deployment mechanism for deploying in one or more parts. 3. The spacecraft according to claim 2, wherein at least one antenna is attached to the fairing. 4. A plurality of the respective antennas are provided in different fairing members among a plurality of fairing members that are provided with a plurality of the antennas and that compose the fairing and are divided into each other when the fairing members are deployed by the deployment mechanism. The spacecraft according to claim 3, characterized in that each is attached. 5. The spacecraft according to claim 4, wherein the antenna is a parabolic antenna. 6. The spacecraft according to claim 2, wherein a plurality of solar cells are attached to the fairing. 7. The spacecraft according to claim 2, wherein a sensor is attached to the fairing.