JPH05201398A - Unfolding structure device for space navigator - Google Patents

Abstract

PURPOSE:To perform suitable unfolding operation of a multistage unfolding structure mounted on a space navigator and to suppress unfolding impact acceleration. CONSTITUTION:An unfolding structure device for a space navigator comprises a fixing tool 4 arranged to a space navigator 1, a hook 5 disposed to a first unfolding structure 21 from the space navigator 1 and engaged with the fixing tool 4, a regulating lever 6 for releasing engagement with the fixing tool 4 through operation of the hook 5 during turn, and a means for releasing the hook 5 from engagement through turn of the regulation lever 6 by stretching a cable 8 when the angle of a second structure 22 coupled to the first unfolding structure 21 attains a given value theta.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a deployable structure device,
In particular, it relates to a device for controlling the operation of a deployable structure used in a spacecraft.

[0002]

2. Description of the Related Art As shown in FIG. 4, a conventional spacecraft 1
The deployment structure 2 such as the solar array paddle mounted on
It is configured to be connected by a plurality of deploying mechanism parts 3, and by the action of this deploying mechanism part 3, the spacecraft 1 is held in a folded state at the time of launch. Then, it is released by a pyrotechnic or the like at a predetermined time on the orbit and deployed. In this case, in order to avoid mechanical interference with the spacecraft 1 as shown in FIG. 5, the deploying structure 2 is provided with pulleys 12 in each deploying mechanism 3 as shown in FIG. By winding the cable 13 around 12, the respective expansion mechanism sections 3 are synchronized.

[0003]

However, such a structure in which the pulley 12 and the cable 13 are synchronized with each other has the following problems. (1) Since the unfolding mechanism 3 is connected by the pulley 12 and the cable 13, the entire unfolding structure may not be unfolded due to a failure in one location of the unfolding mechanism. (2) When the unfolding of the unfolding structure is completed, the unfolding mechanism portions 3 simultaneously complete unfolding, so the unfolding impact acceleration generated in the unfolding structure is very large, and the strength of the unfolding structure is satisfied. The weight is increased. (3) As described above, the attitude of the spacecraft may be disturbed because the expansion impact acceleration is large. An object of the present invention is to provide a deployment structure device that solves such problems, enables a suitable deployment operation, and suppresses deployment impact acceleration.

[0004]

SUMMARY OF THE INVENTION The present invention is directed to a fixture provided on a spacecraft, a hook provided on a first deployable structure from the spacecraft and engaged with the fixture, and a hook. An adjusting lever for releasing the engagement between the hook and the fixture when moved, and a second deployable structure connected to the first deployable structure at a required angle with respect to the first deployable structure. And means for rotating the adjusting lever when it reaches. As means for rotating the lever, a rotating shaft connecting the first deploying structure and the second deploying structure and the adjusting lever are connected by a cable, and the adjusting lever is connected between the cable or the adjusting lever. By interposing a length adjusting tool between the hook and the hook, when the second deployable structure reaches a required angle with respect to the first deployable structure, the tension lever of the cable rotates the adjusting lever to hook. Is configured to be released.

[0005]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Next, the present invention will be described with reference to the drawings. FIG. 1 is a schematic configuration diagram of an embodiment of the present invention.
In the figure, 1 is a spacecraft, 2 is a multi-staged deployable structure, and this deployable structure 2 is connected by a plurality of deploying mechanism units 3 and is stored in the spacecraft 1.
Alternatively, it is designed to be expanded. Here, the device of the present invention is applied to the first unfolded structure 21 provided closest to the spacecraft 1, and the second unfolded structure 22 connected to the first unfolded structure is a predetermined one. Deployment angle θ
The first deployable structure 21 is held on the spacecraft 1 until reaching the angle, and when the deployable angle θ is reached, the deploying operation of the first deployable structural member 21 is started, and as a result, the deployable structure 2 becomes the spacecraft. 1 is configured to be expanded without interfering with 1.

That is, FIG. 2 shows a main part of the device of the present invention. FIG. 2 (a) is a side view before deployment, FIG. 2 (b) is a side view when the deployment structure is deployed, FIG. 6C is a front view of FIG. As shown in these figures, the first deployable structure 21 has a second deployable structure 22 due to the rotary shaft 10.
Are connected. The hook 5 is pivotally supported on the first deployable structure 21, and the hook portion 5a at the tip thereof is engaged with the fixture 4 fixed to the spacecraft 1. An adjusting lever 6 is pivotally supported at a position adjacent to the hook 5 of the unfolding structure 21, one end of the adjusting lever 6 is connected to the other end of the hook 5, and the other end is connected to a cable via a turnbuckle 7. 8
And the cable 8 is connected to the rotary shaft 10. Reference numeral 9 is a guide for the cable 8.

According to this structure, since the hook portion 5a of the hook 5 is engaged with the fixture 4 as shown in FIG. 1 (a) before deployment, as shown in FIG. When the structure 2 starts to be deployed, the first deployable structure 21 is locked to the spacecraft 1 and is not deployed.
Then, as shown in FIG. 2B, the second expanded structure 22
When the expansion angle of θ becomes θ, the cable 8 is pulled along with the movement of the rotary shaft 10, so that the adjustment lever 6 is rotated clockwise in the drawing, and the hook 5 is further rotated clockwise.

As a result, the hook portion 5a of the hook 5 is released from the fixture 4, and the deploying operation of the first deployable structure 21 is started. Therefore, the first deployed structure 21
Is delayed, the interference with the spacecraft 1 as shown in FIG. 5 is avoided. By adjusting the turnbuckle 7, the turning angle of the adjusting lever 6 with respect to the pulling length of the cable 8 is changed, and the turning start time of the hook 5 is changed accordingly, so that the delay angle θ is adjusted. can do.

FIG. 3 shows a modified example of the present invention and is a side view showing the main part thereof. The figure (a) shows the state before the development and the figure (b) shows the state at the time of development, and the portions equivalent to those of FIG. 2 are denoted by the same reference numerals. In this embodiment, the adjusting lever 6 is provided with an adjusting screw 11, and the adjusting screw 11 is brought into contact with the hook 5. Therefore, by changing the screwing position of the adjusting screw 11 with respect to the adjusting lever 6, the turning start point of the hook 5 with respect to the turning angle of the adjusting lever 6 is changed. As a result, the delay angle θ can be adjusted by the adjusting screw 11 instead of the turnbuckle of the above embodiment.

[0010]

As described above, according to the present invention, the hook is provided on the first deployable structure closest to the spacecraft, and the hook is engaged with the fixture provided on the spacecraft, and the second structure is provided. Since the hooks are disengaged when the deployment structure reaches the required angle, it is of course possible to interfere with the spacecraft when the deployment structure deploys. Further, the following effects can be obtained. (1) It is possible to avoid the failure mode of the entire deployable structure due to the failure of the deploying mechanism portion at one place as in the synchronous system. (2) By reducing the impact at the time of the deployment latch, the weight of the deployment structure and the spacecraft is reduced, and the amount of disturbing the attitude of the spacecraft at the time of the deployment latch is reduced. (3) The weight can be reduced by deleting the synchronization mechanism.

[Brief description of drawings]

FIG. 1 is a schematic side view of an embodiment of the present invention.

2A and 2B show essential parts of one embodiment of the present invention, where FIG. 2A is a side view before deployment, FIG. 2B is a side view when deployed, and FIG.
FIG.

3A and 3B show essential parts of a modified example of the present invention, where FIG. 3A is a side view before deployment and FIG. 3B is a side view when deployed.

FIG. 4 is a schematic side view showing the concept of a deployable structure of a spacecraft.

FIG. 5 is a schematic side view for explaining a conventional defect.

FIG. 6 is a schematic side view showing an example of a conventional device.

[Explanation of symbols]

1 Spacecraft 2 Deployment structure 21 1st deployment structure 22 2nd deployment structure 3 Deployment mechanism part 4 Fixture 5 Hook 6 Adjustment lever 7 Turnbuckle 8 Cable 10 Rotation axis

Claims (2)

[Claims] 1. In a spacecraft with a multi-stage deployment structure connected, a fixture provided on the spacecraft and a fixture provided on the first deployment structure from the spacecraft and engaged with the fixture. And the adjusting lever for releasing the engagement between the hook and the fixture when the hook is rotated, and the second expanding structure connected to the first expanding structure is the first expanding structure. And a means for rotating the adjusting lever when it reaches a required angle with respect to an object. 2. The rotating shaft connecting the first expanding structure and the second expanding structure and the adjusting lever are connected by a cable, and between the adjusting lever and the cable or between the adjusting lever and the hook. A length adjuster is interposed between the two, and when the second deployable structure reaches the required angle with respect to the first deployable structure, the tension lever of the cable rotates the adjusting lever to engage the hook. Claim 1 constituted so that it may be released.
Spacecraft deployment structure equipment.