JP3053877B2 - Space deployment structure release device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a space deployment used for discharging and dumping a flexible space deployment structure such as a solar cell paddle or a deployment array mounted on a space vehicle such as an artificial satellite into space. about release detection device of the structure.

[0002]

2. Description of the Related Art Conventionally, in the field of space development,
For example, a deployed structure such as a solar cell paddle that is no longer needed may be released and dumped into outer space to recover the satellite body. Such emission and dumping is performed by separating a connector electrically connected to the satellite main body and separating a connection portion for mechanically connecting the connectors from the satellite main body from the satellite main body.

[0003] Figure 7 shows the release detection device that is used in the mechanical coupling of such release dumped the deployable structure,
This is described in JP-A-64-33000. That is, the deployable structure 2 is removably disposed on the spacecraft 1 via the holding mechanism 3. A guided portion, for example, a guide rail 4 is provided on the deployment structure 2, and a guide portion, for example, a guide roller 5 moves on the guide rail 4.
Guided engagement. The guide roller 5 is supported by the spacecraft 1 via a guide member 6.

[0004] Further, a locking portion 7 is provided on the deployment structure 2, and a cable 8 constituting a release mechanism is locked to the locking portion 7. The cable 8 is engaged with a constant load spring 10 for discharging drive via a pulley 9, and an urging force is applied through the constant load spring 10 in the arrow Y direction.

When the deployment structure is discharged and dumped, the holding mechanism 3 is first operated to release the deployment structure 2.
Is released. Then, the constant load spring member 10 winds up the cable 8 and urges the deployed structure to move in the arrow Y direction. As a result, the deployed structure 2 is transported with the guide rails 4 guided by the guide rollers 5, and the spacecraft 1 is moved.
It is more dumped.

[0006] However, above Kiho detection device, by the guide rails 5 of the space navigation side is engaged constantly engaged with the guide rails 4 of the deployable structure side, Ya shock applied when the launch from the ground into space Due to intermittently receiving a high load due to the vibration, damage or the like is caused, and there is a possibility that it is difficult to reliably discharge and dump the deployment structure 2.

[0007]

As described above [0005] In the conventional release detection device is damaged when it is transported into space, with the problem of emission dumping operation becomes difficult.

[0008] The present invention has been made in view of the above circumstances, in the configuration simple, and to provide a release detection device of space expansion Structures manner can realize reliable release dumping operation .

[0009]

SUMMARY OF THE INVENTION The present invention provides a holding means for releasably holding a space deployable structure on a spacecraft, and a space deployable structure provided on one of the spacecraft or the space deployable structure. A guide for release, and a guide corresponding to the guide on the other of the space vehicle or the space deployable structure.
And a second guide that is movably guided by the guide section.
Move between the first position and the second position separated from the guide portion
A guided portion provided so as to be able to be provided, and the guided portion is connected to the first
To move to the above position and engage with the guide part so that it can move freely.
Biasing means for causing, the guided portion or the guide portion to decide located at the second position against the biasing force of the biasing means
Position regulating means for separating the holding means, and holding and releasing of the holding means
The guided part is interlocked with the urging force of the urging means.
Positioning the position restricting means so as to be movable to the first position.
And canceling means for canceling the fit, the guided portion in conjunction with the positioning <br/> release of said position regulating means in biasing force of the biasing means
Driving in a state where it is engaged with the guide part so as to be able to move freely
And guide the guided portion to move along the guiding portion.
And a release means for releasing the space deployable structure from the spacecraft to form a space deployable structure release apparatus.

[0010]

According to the above construction, the guided portion is regulated to the second position by the position regulating means against the urging force of the urging means, is separated from the guiding portion, and is released when the position regulation is released. By moving to the first position by the urging force of the urging means and engaging with the guide, the deployable structure is guided by the guide, and is transported and discharged from the spacecraft. Therefore,
Protection against a high load due to an impact or the like when transporting the guided portion to the outer space can be achieved, the damage or the like can be reliably prevented, and a reliable discharge operation can be realized.

[0011]

Embodiments of the present invention will be described below in detail with reference to the drawings.

FIG. 1 shows an apparatus for discharging a space deployable structure according to one embodiment of the present invention. A guide portion for discharging and dumping, for example, a guide roller 20 provided on the spacecraft side is provided with the deployable structure 2. Is provided so as to be able to freely contact and separate from the guide rails 4 provided in the above. In FIG. 1, with the same parts as FIG. 7 are denoted by the same reference numerals, and detailed description thereof is omitted.

That is, the guide roller 20 which is a feature of the present invention is rotatably supported by the support member 21 via the bearing 22. The support member 21 is disposed on a support base 24 via a rotation shaft 23 so as to be rotatable in the directions of arrows A and B. The support base 24 is fixed to the spacecraft 1. And
A spring member 25 is provided between the support base 24 and the support member 21,
It is engaged so as to apply the biasing force in the direction of the guide rail (the direction of arrow A). As shown in FIG. 2, a lock pin 26 is provided on the support base 24 via a spring member 27 so as to be able to move in and out, and a lock hole 21a is formed in the support member 21 corresponding to the lock pin. You. As a result, the support member 21 is rotated through the rotation shaft 23, and when the support member 21 is rotated to a predetermined position, the lock pin 26 is inserted into the lock hole 21 a with the guide roller 20 engaged with the guide rail 4. Are engaged and positioned.

Further, as shown in FIG.
An intermediate portion of a rotating member 29 is provided via a shaft 28 so as to be rotatable in the directions of arrows C and D. The rotating member 29 has a pulley 30 rotatably supported at one end and a locking portion 29a at the other end.
Is formed. The locking portion 29a corresponds to the engaging portion 21b formed on the support member 21, as shown in FIG. On the other hand, the pulley 30 is engaged with an intermediate portion of a wire rope 31 for position control, and an urging force is applied through the wire rope 31 in the direction of arrow D as shown in FIG. As a result, the pulley 30 rotates the rotating member 29 in the same direction around the axis to engage the locking portion 29 a with the engaging portion 21 b of the support member 21, and presses the support member 21 against the urging force of the spring member 25. The support member 2 is urged to rotate in the direction of arrow B against
The first guide roller 20 is urged to rotate to a position shown by a two-dot chain line in FIG.

The wire rope 31 is connected to an intermediate pulley 32
Through a cutting mechanism such as an explosion bolt (not shown) (see FIG. 5). When cut through this cutting mechanism (not shown), the pulley 30 is supported by the supporting member 2.
The tension required to separate the one guide roller 20 from the guide rail 4 provided on the deployment structure 2 is applied.

In the above configuration, the wire rope 31 is usually given a predetermined tension via the intermediate pulley 32, and the tension is used to urge the pulley 25 in the direction of arrow D to move the rotary member 29 in the same direction. Is urged to rotate. As a result, the rotating member 29 is supported by the support member 21 via the locking portion 29a.
Of the arrow B against the urging force of the spring member 25.
To rotate the guide roller 20 away from the guide rail 4 (indicated by a two-dot chain line in FIG. 1A).

When the deployed structure 2 is discharged and dumped, a command signal is first input to a control unit (not shown), and in response to this, the cutting mechanism (not shown) is operated, and the wire rope 31 is moved. Be cut off. Thereby, the pulley 30 of the rotating member 29 becomes free. Then, the support member 21
Is rotated in the direction of arrow A by the urging force of the spring member 25,
The engaging portion 21b pushes the locking portion 29a of the rotating member 29 so as to kick it off (see FIGS. 4A and 4B), and urges the rotating member 29 in the direction of arrow C. It is further rotated in the same direction. When the support member 21 and the guide roller 20 are engaged with the guide rail 4, the lock pin 26 is engaged with the lock hole 21a, and the engagement position is secured. Here, as described above, first, the holding mechanism 3 is actuated to release the holding of the deployed structure 2, the cable 9 is wound up by the constant load spring member 10, and the deployed structure 2 is moved in the arrow Y direction. It is energized to move. As a result, the deployed structure 2 is transported with the guide rails 4 guided by the guide rollers 20, and discharged and dumped from the spacecraft 1.

As described above, the discharging device of the space deployable structure restricts the position of the guide roller 20 at a position separated from the guide rail 4 against the urging force of the spring member 25, and the position restriction is released. Then, the movable structure is moved and urged by the urging force of the spring member 25 to be engaged, so that the deployed structure 2 is guided by the guide rail 4 to be transported and discharged and dumped from the spacecraft 1. . According to this, protection against a high load due to an impact or the like when the guide roller 20 is transported to outer space can be achieved, and the occurrence of damage or the like is reliably prevented, so that reliable control of the discharge and dumping operation is realized. You.

In the above-mentioned space deployable structure discharge apparatus, when the revolving structure 2 and the spacecraft 1 are to be assembled on the ground before they are launched into space, the guide rail 4 and the guide roller 4 are used. 20 can be easily combined, so that the handling including the assembling work can be simplified.

In this embodiment, the rotating member 29 is used.
The pulley 30 is provided on the wire rope 31, and the pulley 30 is engaged with the wire rope 31 to restrict the position of the rotating member 29. However, as shown in FIG.
It is also possible to link one end of the wire rope 31 to the link 9 via a link connecting member 32 so as to regulate the position using the tension of the wire rope 31.

In the above embodiment, the guide roller 20 constituting the guide section is provided on the spacecraft side, and the guide rail 4 constituting the guided section is provided on the deployed structure 2. The present invention is not limited to this, and it is also possible to arrange the guide roller 20 and the guide rail 4 in reverse. The guide portion and the guided portion are not limited to the guide roller 20 and the guide rail 4, and various types can be configured.

Further, in each of the above embodiments, the position of the rotating member 29 is regulated by using the wire rope 31. However, the present invention is not limited to this, and various configurations are possible.

Therefore, it is needless to say that the present invention is not limited to the above-described embodiment, and that various modifications can be made without departing from the scope of the present invention.

[0024]

As described above in detail, according to the present invention, it is possible to provide a space deployable structure discharge apparatus which can realize a reliable discharge and dumping operation with a simple structure.

[Brief description of the drawings]

FIG. 1 is a view showing an apparatus for discharging a space deployable structure according to an embodiment of the present invention.

FIG. 2 is a diagram showing a part of FIG.

FIG. 3 is a diagram showing a partial plane of FIG. 1;

FIG. 4 is a diagram showing a partial operation state of FIG. 1;

FIG. 5 is a diagram showing a position regulation state in which the guide roller of FIG. 1 is separated from the guide rail.

FIG. 6 is a diagram showing another embodiment of the present invention.

FIG. 7 is a view for explaining a problem of a space deployable structure to which the present invention is applied.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 3 ... Holding mechanism part, 4 ... Guide rail, 7 ... Locking part, 8 ... Cable, 9 ... Pulley, 10 ... Constant load spring, 20 ... Pulley, 21 ... Support member, 21a ... Lock hole, 21b ... Engaging part , 22 ... bearing, 23 ... rotating shaft, 24 ... support base, 25 ...
Spring member, 26 ... lock pin, 27 ... spring member, 28 ...
Shaft, 29 ... rotating member, 29a ... locking part, 30 ... pulley,
31: wire rope, 32: intermediate pulley, 33: link connecting member.

Claims (1)

(57) [Claims] 1. A releasably Space deployable structure to space vehicle
Holding means for holding the said the other of said space vehicle or the space while a guide portion of the space deployable structure for releasing provided on the deployable structure, the space vehicle or the Space deployable structure
It is provided corresponding to the guide part and can be moved and guided by the guide part
And a second position spaced from the guide.
And a guided portion movably provided between the positions, and the movable portion biases the guided portion to the first position to guide the guided portion.
Urging means for movably engaging with the section, and the second section opposing the guided section against the urging force of the urging means.
And position regulating means for spacing from the guide portion to decide located in position, the said guided portion in conjunction with the retention release of the holding means
And release means for releasing the positioning of the movable front <br/> Symbol position regulating means to said first position by the biasing force of the biasing means, the guided portion in conjunction with the release position of the position regulating means Move guidance to the guide section by the urging force of the urging means
The space-deployed structure is driven while being freely engaged, and moves and guides the guided portion along the guide portion to move the space deployment structure
A discharge device for a space deployable structure, comprising: a discharge means for discharging from a spacecraft.