JP2001114198A - Binding cable packaging structure of expanding structure of aerospace vehicle - Google Patents

Abstract

PROBLEM TO BE SOLVED: To prevent a binding cable from being formed into debris in the releasing of the binding cable holding an expanded structure. SOLUTION: The binding cable 1 is disposed between an artificial satellite 6 and an expanded structure while being attached to the expanded structure 3, thereby holding the expanded structure 3. With the operation of a release mechanism part 4, the expanded structure is released to start expanding. The binding cable 1 is expanded together with the structure 3 without separating from the expanded structure by a holding point 2 of the expanded structure 3. In this case, one side of the binding case 1 is regulated by the artificial satellite and the other thereof is regulated by the holding point of the expanded structure, whereby release (debris) of the binding cable 1 to the aerospace can be prevented. The binding cable 1 is kept from causing interference with the other apparatus carried on the artificial satellite and prevented from interference with the expanded structure.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a restraining cable mounting structure for a deployment structure for a spacecraft.

[0002]

2. Description of the Related Art Deployable structures for space vehicles (for example, solar battery paddles and antennas for satellites) are folded when launched from the ground, and are generally deployed in outer space. It is. Therefore, the deployed structure is restrained in a folded state until it reaches outer space. One typical method of restraining is to use a restraining cable.

Conventionally, in a method using a restraining cable, a deployed structure is simply restrained from outside by a restraining cable,
This is released in outer space to deploy the deployable structure. As shown in JP-A-5-213289 and JP-A-3-29000, in the related art, a restraining cable is mounted outside a deployment structure, and both ends of the restraining cable are connected to a release mechanism. ing.
At this time, tension is applied to the restraining cable to hold the structure. When the structure was deployed, the connection of the restraining cable was released simultaneously with the operation of the release mechanism, and the deployed structure was released into outer space due to the recoil of the restraining cable tension.

[0004]

In the prior art in which the restraining cable is surrounded and restrained from the outside of the deployment structure, when the structure is deployed, the restraining cable is discharged into outer space. The released restraint cable turned into debris (garbage in outer space).

Accordingly, an object of the present invention is to provide a constrained cable mounting structure for a spacecraft deployable structure that does not release a restraint cable to outer space even when the spacecraft structure is deployed in space. To provide.

[0006]

According to the present invention, the restraining cable is arranged so as to be attached to the deploying structure instead of holding the deploying structure from the outside by the restraining cable, and the deploying structure is held. The constrained cable mounting structure of the deployable structure for a spacecraft can be obtained.

In the present invention, when one side of the restraining cable is connected to the release mechanism of the satellite and the other side is fixed to the satellite, the restraining cable is arranged so as to pass through the holding point of the deployable structure. Needless to say, it also has the same expanded structure holding function as the above. Further, since the holding point also has a function of a guide, the movement of the restraining cable after the structure is deployed can be restrained. In the present invention, when one side of the restraining cable is disconnected from the satellite, the deployment structure starts deployment. The other side of the restraining cable remains fixed to the satellite and unfolds with the deployment structure as the restraining cable passes through the holding point (guide). As a result, the restraint cable is not released into outer space.

[0008]

Next, embodiments of the present invention will be described in detail with reference to the drawings.

FIG. 1 is a plan view of one embodiment of the present invention, and shows the entire configuration when a restraining cable is mounted between an artificial satellite and a structure. In FIG. 1, 1 is a restraining cable, 2 is a holding point, 3 is a deployed structure, 4 is a restraining cable releasing mechanism, 5 is a restraining cable fixing point, and 6 is an artificial satellite.

The operation will be described. First, in FIG.
The restraining cable 1 is set so as to hold the deployment structure 3. Next, a tension necessary for holding the developed structure 3 is applied to the restraining cable 1. Here, the restraining cable 1 is set so as to pass through a holding point (which also has a guide function) 2 arranged on the satellite side of the deployment structure 3.

FIG. 2 is an explanatory diagram showing a state after the deployment structure has been deployed. The reference numerals in FIG. 2 correspond to the reference numerals in FIG. As shown in FIG. 2, one side of the restraint cable 1 is released by the operation of the release mechanism 4, and the structure starts to deploy. At this time, since the restraining cable 1 has passed through the holding point / guide 2 of the deployment structure 3, it is deployed together with the deployment structure 3. Thereby, the restraint cable 1
The problem of becoming debris is solved. In addition, since the restraining cable 1 is fixed to the deployable structure 3, it is possible to prevent interference with artificial satellite equipment and the deployable structure.

In the embodiment described above, the holding point is arranged on the satellite side of the deployable structure 3 and the restraining cable is mounted between the artificial satellite and the deployable structure. It is also possible to arrange the holding point on the opposite side of the deployment structure 3 from the satellite and to mount the restraining cable outside the deployment structure, if this is not compromised. Alternatively, the holding points may be arranged inside the deployment structure 3 and the restraining cable may be mounted inside the deployment structure. In the embodiment, nothing is mounted between the guides at several places. However, by mounting a coil spring here, excessive slack of the restraining cable can be suppressed.

[0013]

An advantage of the present invention is that debris emission into space can be prevented even in a spacecraft deployable structure using a restraining cable.

The reason for this is that by fixing one side of the restraining cable and deploying it together with the deploying structure, the restraining cable can be deployed without being released.

[Brief description of the drawings]

FIG. 1 is a configuration diagram (plan view) showing an overall configuration of an embodiment of the present invention.

FIG. 2 is a plan view showing a developed state of the embodiment shown in FIG. 1;

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Constraint cable 2 Holding point / guide 3 Deployment structure 4 Constraint cable release mechanism 5 Constraint cable fixing point 6 Satellite

Claims (4)

[Claims] 1. A constraining cable mounting structure for a spacecraft deployable structure, wherein the restraint cable is arranged so as to be attached to the deployable structure and holds the deployable structure. 2. When connecting one end of the restraining cable to the release mechanism on the spacecraft side and fixing the other end to the spacecraft,
A constrained cable mounting structure for a spacecraft deployable structure, wherein the restraint cable is disposed so as to pass through a holding point of the deployable structure. 3. The space navigation system according to claim 2, wherein when the deployment structure is deployed by disconnecting one side of the restraining cable from the space vehicle by the release mechanism, the restraining cable continues to be held by the holding point. Restricted cable mounting structure for body deployment structure. 4. A constrained cable mounting structure for a spacecraft deployable structure that retains the deployable structure by passing the restraint cable through a holding point attached to the deployable structure.