JPH05294297A - Construction of large-sized cosmos structure article - Google Patents

Abstract

PURPOSE:To construct a large-sized cosmos structure article which can be efficiently mounted in the space in a rocket, in a short construction period, with a low construction cost, and in a simple method. CONSTITUTION:A large-sized cosmos structure article is equipped with a base member 1 installed in rotatable manner on a rotary shaft 2 and lamination panels 3 and 5 each of which is formed by folding a number of solar battery panels 7 and is transported into the cosmos space by a rocket in the state where a plurality of lamination panels 3 and 5 are installed alternately on the outer periphery of the base member 1, and in the cosmos space, the base member 1 is revolved, and each centrifugal force is generated on the lamination panels 3 and 5, and the solar battery panel 7 is developed, and the a plurality of lamination panels 3 and 5 are developed in planary form.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a construction method for constructing a large planar structure such as a solar power generation satellite and a platform in outer space.

[0002]

2. Description of the Related Art In recent years, solar power generation satellites in outer space,
There is an increasing need to build large flat structures such as platforms. In order to construct such a large-scale structure, the structure has a system that can be mounted on a rocket, and furthermore, it has a unique technical problem that it must be assembled in outer space under zero gravity.

The first method conventionally considered for constructing such a large space structure is to mount a solar cell panel on a truss in advance, fold the truss, mount it on a rocket, and transport it to the space. The second method is a method of deploying trusses in space to construct solar power generation satellites.
A method of constructing a solar power generation satellite using EVA (astronaut's extravehicular activity) or FTS (free flying robot) in space after mounting and transporting the solar cell panel and truss on the rocket separately. Is.

[0004]

However, in the first method of folding the truss described above, when the number of solar cell panels is large, there is a lot of wasted space when the solar cell is folded and mounted on the rocket, and the launch cost of the rocket is increased. It is disadvantageous from the standpoint of construction, and because the large planes connected in series are constructed at the same time during construction, there is a risk of inducing vibration of the truss and solar panel due to the construction operation, and it is stable as a structure. There is room for consideration from the viewpoint of sex.

In the second method of transporting the solar cell panel and the truss in separate states, the solar cell panel and the truss can be efficiently mounted on the rocket, but in the case of construction by EVA. ,
There is a problem in safety because astronauts are exposed to the outer space where there is a risk of radiation and debris for a long time. In addition, truss assembly work in space using FTS,
Robots are required to carry out solar panel installation work assuming complicated intelligence, which is difficult on the ground.

The present invention solves the above-mentioned problems, and can be efficiently mounted in the space inside the rocket.
An object of the present invention is to provide a construction method capable of constructing a large space structure by a simple method with a short construction period, a low construction cost and a simple method.

[0007]

Therefore, the method for constructing a large space structure according to the present invention is formed by folding a base member 1 rotatably provided on a rotary shaft 2 and a large number of solar cell panels 7. A plurality of laminated panels 3 and 5 are attached to the outer periphery of the base member 1 in the vertical direction alternately in the vertical direction, and are transported to outer space by a rocket. By rotating, the centrifugal force is generated in the laminated panels 3 and 5, the solar cell panel 7 is expanded, and a plurality of laminated panels 3,
5 is developed in a plane shape.

It should be noted that the numbers added to the above-mentioned constitutions are for comparison with the drawings for easy understanding, and the constitutions of the present invention are not limited thereto.

[0009]

In the present invention, for example, as shown in FIG.
When the base member 1 is rotated about the rotating shaft 2, the rotation of the base member 1 causes a centrifugal force to be generated in the upper laminated panel 3 and the lower laminated panel 5, so that the folded solar cell panel 7 moves in the direction A in the figure. When unfolded, the upper laminated panel 3
And the lower laminated panel 5 itself rotates in the direction B in the figure, and as shown in FIG. 5, a solar power generation satellite having an octagonal plane is constructed.

[0010]

Embodiments of the present invention will be described below with reference to the drawings. In addition, although an example of constructing a solar power generation satellite is shown in the present embodiment, it is also applicable to other large planar structures such as a platform.

1 to 3 show an embodiment of a solar power generation satellite according to the present invention. FIG. 1 is a perspective view showing a state of being housed in a rocket, FIG. 2 is a plan view of FIG. 1, and FIG. It is a partial side view which shows the connection structure of a solar cell panel.

In FIGS. 1 and 2, the base member 1 is rotatably arranged on a rotary shaft 2, and a motor (not shown) provided in the base member 1 causes the base member 1 and the rotary shaft 2 to rotate. Are relatively rotatable. An upper laminated panel 3 and a lower laminated panel 5 are attached to the outer periphery of the base member 1 by a support member 6. In this embodiment, each of the upper laminated panel 3 and the lower laminated panel 5 has four sets, but the number of sets is arbitrary.

The laminated panels 3 and 5 are, as shown in FIG.
A large number of solar cell panels 7 are connected by a hinge 9. In FIGS. 1 and 2, a state in which a large number of solar cell panels 7 are folded is shown, and the solar cell panels 7 are folded by changing the area thereof. The laminated panels 3 and 5 are trapezoidal and the trapezoidal upper side, that is, the solar cell panel 7 having the smallest area is attached to the base member 1 via the support member 6. The upper laminate panel 3 and the lower laminate panel 5 are alternately arranged around the base member 1 so that the upper laminate panel 3 and the lower laminate panel 5 do not interfere with each other.

Next, a method for constructing the solar power generation satellite carried by a rocket in outer space will be described with reference to FIGS. 4 and 5. FIG. 4 is a conceptual diagram for explaining the construction method, and FIG. 5 is a plan view of the constructed solar power generation satellite.

The solar power generation satellites shown in FIGS. 1 and 2 are
After placing it on an appropriate orbit in outer space, as shown in Fig. 4,
The base member 1 is rotated about the rotating shaft 2. This rotation energy is only required to generate the first rotation, and the rotation of the base member 1 causes the upper laminated panel 3 to rotate.
A centrifugal force is generated in the lower laminated panel 5 and the folded solar cell panel 7 is developed in the direction A in the figure, and the upper laminated panel 3 and the lower laminated panel 5 themselves rotate in the direction B in the figure. As shown in FIG. 5, a solar power generation satellite composed of an octagonal plane is constructed.

Next, another embodiment of the present invention will be described with reference to FIGS. 6 is a plan view of the primary deployment, FIG. 7A is a partial front view of FIG. 6, FIG. 7B is a partial plan view of FIG. 6, FIG. 8 is a state of the secondary deployment, and FIG. FIG. B is a partial plan view.

In this embodiment, as shown in FIG.
The laminated panel 10 includes three laminated panels 10a, 10b,
It is divided into 10c, is folded by a hinge 11, and is rotatably connected. Further, as shown in FIG. 8, a hinge 12 for primary deployment is attached to the laminated panels 10a and 10c. Such a laminated panel 10 is shown in FIGS.
It is attached to the base member 1 in the same manner as. When stored in the rocket, the laminated panels 10a, 10b, 10c are folded and unfolded as shown in FIG. 6 at the time of the first unfolding. The motor is rotated by a motor not to be developed into the state shown in FIG. Therefore, according to the present embodiment, it is possible to further store a vehicle having a large deployment area in the rocket.

[0018]

As is apparent from the above description, according to the present invention, a base member rotatably provided on a rotary shaft,
Having a laminated panel formed by folding a large number of solar cell panels, with a plurality of laminated panels alternately attached to the outer periphery of the base member in the vertical direction, transported to outer space by a rocket, in outer space, By rotating the base member, a centrifugal force is generated in the laminated panel, the solar cell panel is developed, and the plurality of laminated panels are developed in a planar manner. It is performed only by the centrifugal force generated by the rotational movement, does not require dangerous assembly work such as EVA, and can be folded and stored in the rocket, so that it can be efficiently mounted in the space inside the rocket.
The construction period is short, the construction cost is low, and a large space structure can be constructed by a simple method.

[Brief description of drawings]

FIG. 1 is a perspective view showing an embodiment of a solar power generation satellite according to the present invention and showing a state of being housed in a rocket.

FIG. 2 is a plan view of FIG.

FIG. 3 is a partial side view showing a solar cell panel connection structure.

FIG. 4 is a conceptual diagram for explaining a construction method according to the present invention.

FIG. 5 is a plan view of a solar power generation satellite constructed according to the present invention.

FIG. 6 is a plan view showing the other embodiment of the present invention in the first development.

7 is a partial front view of FIG. 6, and FIG. B is a partial plan view of FIG.

FIG. 8 shows a state in which a secondary deployment is performed from the state of FIG. 6, FIG. A is a partial front view, and FIG. B is a partial plan view.

[Explanation of symbols]

1 ... Base member, 2 ... Rotating shaft, 3 ... Upper laminated panel, 5
... Lower laminated panel 6 ... Support member, 7 ... Solar cell panel, 9, 11, 12 ...
Hinge 10 ... Laminated panel

Claims (1)

[Claims] 1. A base member rotatably provided on a rotating shaft, and a laminated panel formed by folding a large number of solar cell panels, wherein a plurality of laminated panels are vertically arranged alternately on the outer periphery of the base member. In the mounted state, it is transported to outer space by a rocket, and in the outer space, by rotating the base member, centrifugal force is generated in the laminated panel to deploy the solar cell panel and the plurality of laminated panels. A method for constructing a large space structure, which is characterized by deploying a plane.