JPH03197300A - Expanding structure for space - Google Patents

Abstract

PURPOSE:To simplify the expansion mechanism of an expanding structure by inserting several cylindrical expanding members of different diameter in each ether freely expandable successively, keeping respective space between them airtight, and expanding the expanding structure with an expansive force propor tional to the pressure difference between sealed-in gas and the space. CONSTITUTION:When an expanding structure is helded in an enclosed state, expanding members are arranged concentric to each other in the order of inner- most 1a, 1b-1d, and airtight seals 2 are provided between respective expanding member 1a-1d, and distance between them are kept constant by means of guides 9 respectively. The enclosed state is maintained with a releasing mechanism 4 locked to a receiving portion 5 on the expanding member. When the expanding structure held in the enclosed state is loaded on an artificial satellite or the like and launched in the space, locking of the releasing mechanism 4 is released to expand the expanding members by means of guides 9 along a guide rail 10 with an expansive force proportional to the difference between the pressure of air 3 sealed in the spaces between the expanding members 1a-1d (atmospheric pressure) and the environmental pressure.

Description

[Detailed Description of the Invention] [Field of Industrial Application] This invention relates to a deployable structure deployed in outer space, such as a support structure for a sub-reflector of a large antenna used in an artificial satellite or a space base. It is something.

[Conventional technology]

Structures such as antennas used in artificial satellites and space bases tend to become larger due to increasingly sophisticated mission requirements. On the other hand, rockets used to launch satellites and other satellites are also becoming larger, but this progress is slower than the increase in the size of structures such as antennas.

When launching an artificial satellite carrying a structure such as a large antenna, it is necessary to fold the structure such as the antenna and store it in a rocket. moreover.

In space, it is necessary to unfold structures such as folded antennas and maintain them in the desired shape and shape.

FIG. 5 is a perspective view showing an example of a conventional space deployable structure. In FIG. 92, (1a) to (1d) are deployable members with different diameters! 7. (6a) is a pulley fixed to the top of each deployable member (6b) is a pulley fixed to the bottom of each deployable member, +7+ is fixed to the innermost deployable member (1a), and is fixed to each deployable member. Cable connected to Citram+81 through pulley, (8)
(9) is a drum that rotates multiple times by power to wind up the cable (7); (9) maintains a constant interval between adjacent deployment members;
Guides Ql are installed in a radial manner in order to smooth the deployment movement. Ql is a guide rail that is attached in the deployment direction of the deployment member and guides the deployment movement of the guide (9).

Next, the operation will be explained. Fig. 6 shows a cross-sectional view of the conventional space deployable structure in its stored state, with the deployable member (1a) being the innermost, and the following (1b) to (1d).
) are arranged concentrically in this order.

The respective intervals are kept constant by a guide (9).

The cable (7) is in a fully extended state.

As shown in Fig. 1, the operation when unfolding is to rotate the drum (8) around the rotation axis +Ill by power, and connect the cable (
7) onto the drum (8). Since the cable (7) is connected to each deployment member via pulleys (6a) (6b), by winding the cable (7) around the drum (8), the pulley ( 6
a) The length of the cable (7) passing through (6b) is L in Figure 6.
1. The guide (9), which is short as L' in FIG. 1, is guided by the guide rail αG while each deploying member rises, thereby enabling the deploying operation.

[Problem to be solved by the invention]

Conventional space deployable structures are configured as described above, so a drum (8) and a cable (7) are used for deployment.
, since pulleys (6a) (6b) are required.

There were problems in that it was heavy and required energy to deploy the entire deployable structure.

This invention was made to solve the above-mentioned problems, and it is possible to reduce the weight by omitting a device for deploying a structure, and to create a device that can deploy a structure with only a small amount of energy. The purpose is to obtain.

[Means to solve the problem]

The space deployable structure according to the present invention has an airtight seal on each deployable member, seals gas inside the deployable member, and has a holding/releasing mechanism that enables deployment when necessary. be.

[Effect]

The deployable structure according to the present invention has an airtight seal on the deployable member, and by sealing gas inside the deployable member,
Deployment is made possible in the vacuum state of outer space by the pressure difference between the inside of the deployable member and outer space, and the deployment timing is controlled by a holding and releasing mechanism.

〔Example〕

An embodiment according to the present invention will be described below with reference to the drawings. In Fig. 1, (1a) to (1b) are deployable members with different diameters, (2) is an airtight seal installed on each deployable member, and (3) is a deployable member (1a) to (1b). ) and the gas sealed in the deployable member by the airtight seal (2), (4) is a holding and releasing mechanism for controlling the deployment timing of the deployable structure, and (5) is a holding and releasing mechanism fixed to the deployable member. This is the receiving part of the holding/releasing mechanism that comes in contact with the holding/releasing mechanism.

Next, the operation of the above embodiment will be explained as follows:
An example will be explained in which the pressure is equal to the atmospheric pressure on the ground in the stored state.

FIG. 2 shows a cross-sectional view of the space deployable structure according to the present invention in a stored state. The deployable members are arranged concentrically in the order of (1b) to (1d), with (1a) being the innermost part. The distance between the two is kept constant by the guide (9), and the stored state is maintained when the holding and releasing mechanism (4) touches the receiving part (5) on the expansion member (K). It is maintained.

When the deployable structure is on the ground, the pressure of the sealed gas (3) inside the deployable member is equal to atmospheric pressure, so no deployment force is exerted, but when an artificial satellite or the like carrying the deployable member is launched by a rocket, etc. As the altitude increases, the external pressure decreases, so a deployment force proportional to the difference between the pressure of the sealed gas +31 inside the deployment member and the outside pressure acts on the entire deployment member. Even if the deployment force acts on the deployment member, it is not the time to deploy the deployment structure.

By keeping the holding and releasing mechanism (4) in contact with the receiving portion (5) on the deployable member, the deployable structure can be maintained in the stored state.

FIG. 3 shows a cross-sectional view of the deployable space structure according to the present invention in the deployed state. When released, the guide (9) is guided to the guide rail αG by a deployment force proportional to the difference between the pressure of the sealed gas (3) in the deployment member and the outside air pressure, and the deployment structure is deployed. Especially since outer space is almost a vacuum.

Since there is a large pressure difference with the pressure of the sealed gas (3) in the deployable member, the deploying force is large, and there is no gravity, the deployable structure can be deployed very easily.

In addition, in the above embodiment, the gas (3
) is shown to be equal to the atmospheric pressure on the ground in the stowed state, but it may be higher than the atmospheric pressure on the ground, and in that case, the deployment force of the deployable structure is equal to the pressure of the enclosed gas (3). In the stowed state, the pressure is greater than when it is equal to the atmospheric pressure on the ground.

Further, in the above embodiment, four deployable members (1a) to (1d) are shown, but the number of deployable members may be any number as long as it is two or more, and the same effect as in the above embodiment can be achieved. .

Furthermore, the holding and releasing mechanism is not limited to the shape and form shown in the above embodiments.2For example, the holding and releasing mechanism 04 and the receiving part α9 of the holding and releasing mechanism may be provided on each deployable member as shown in FIG. Needless to say, this effect can be obtained.

〔Effect of the invention〕

As described above, according to the present invention, the deployable structure is configured to be deployed by a deploying force proportional to the pressure difference between the pressure of the gas sealed in the deployable member and the external pressure. It does not require any special equipment and can be lightweight. Furthermore, the energy required to drive the holding and releasing mechanism is less than the energy required to deploy the entire deployable structure, so there is an effect that less energy is required for deployment.

[Brief explanation of drawings]

FIG. 1 is a perspective view showing a deployable space structure according to an embodiment of the present invention, FIG. 2 is a cross-sectional side view of the space deployable structure in its stored state, FIG. FIG. 5 is a perspective view showing a conventional deployable structure for space; FIG. 6 is a cross-sectional side view in the stored state; FIG. 7 is a cross-sectional side view in its unfolded state. In the figure, (Ia) to (1b) are deployable members with different diameters, (2) is an airtight seal attached to each deployable member, and (3) is a deployable member (1a) to (1b).
) and the gas sealed in the deployable member by the airtight seal (2), (4) is a holding and releasing mechanism for controlling the deployment timing of the deployable structure, and (5) is a holding and releasing mechanism fixed to the deployable member. The contacting holding and releasing mechanism receiving parts (6a) are pulleys fixed to the upper part of each deployable member; (6b) are the pulleys fixed to the lower part of each deployable member; and (6b) are the pulleys fixed to the lower part of each deployable member; a cable (8) fixed and connected to the drum (8) through a pulley fixed to each deployment member;
is a drum that rotates by power and winds up the cable (7);
The ninth guide GG, which smoothes the deployment operation, is a guide rail that is attached in the deployment direction of the deployment member and guides the guide (9). Note that the same reference numerals in Figure 1 indicate the same or equivalent parts.

Claims (1)

[Claims] a plurality of deployable members each having a hollow interior with a different diameter;
an airtight seal placed between adjacent deployable members to ensure airtightness between the deployable members; a gas sealed inside the plurality of deployable members and the airtight seal; and a deployable member placed between the adjacent deployable members. a guide that maintains a constant interval between the two; a guide rail that is installed in the direction of deployment of the deployable member to smooth the movement of the guide; A space deployable structure comprising: a holding/releasing mechanism that guides the unfolding movement of the spacer; and a receiving part installed on the deploying member and in contact with the holding/releasing mechanism in the stored state to maintain the stored state.