JPS6359920B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a fastener for solar panels of multiple self-expanding plates folded into a stacked structure, primarily spacecraft.

A solar panel suitable for the above-mentioned applications is a large flat plate, for example 2x3 or more in area, on one side of which solar cells for generating electrical energy are installed. A large number of solar cells are often required to meet the electrical current needs of a spacecraft. Therefore, it is necessary to equip a large number of flat plates as described above. For example, because space is limited inside transport objects such as rockets and spacecraft, individual solar panels are folded into an accordion shape and unfolded only after reaching space.

The stack structure must be bundled and secured to the spacecraft during the orbit change. Otherwise, the solar panels or solar cells in the flying object will be damaged due to the unavoidable vibrations that occur during launch. In space, solar panels must be deployed no matter what the conditions are. Otherwise, the flight mission will fail.

It is known to hold the plate fixedly with a pivotable arm and to release the plate from this fixation by pivoting the arm away from the stacked structure.
However, according to this principle, a large number of movable parts are connected, which increases mechanical costs. In addition,
Location and weight concentrations occur, with a corresponding penalty in the balance of the actual loads.

Secondly, in the case of more than 4 to 5 solar panels, the angle range when releasing them is extremely large, so when the number of solar panels increases, it is impossible to introduce the above-mentioned known fasteners. Become.

The object of this invention is to create a reliable space flight object that can be secured even when the number of solar panels increases, is lightweight, has a small number of structural members, saves installation space, and is lightweight. The purpose of the present invention is to provide fasteners for solar panels.

The above problem consists of a fixed tension device in which the fastener is fixed to the frame of the outermost solar panel, a release device installed on the spacecraft, and a release device that is rotatably attached to the fixed tension device, and after release the fixed tension device. a metal belt having a spring characteristic, the free end of which is coiled up to the device, the free end of the metal belt being locked to a release device, and tension being applied to the belt after locking; This problem is solved by bundling stacked structures.

The device of the invention provides a highly efficient clamping of a solar panel of a spacecraft that requires only a small amount of energy to release. After release, all parts fall into place without difficulty, eliminating any disturbances or negative effects on the trajectory of the spacecraft. Operation at the ground station is extremely simple and can be carried out without the need for expensive auxiliary equipment. No problems arise when implementing this fastener for individual devices.

This invention will be explained in more detail based on one drawing.

The fastener according to the present invention includes a pair 10 of metal belts 11 and 12 having coiled spring characteristics as shown by the dashed line in the figure in a substantially released state, and one end of the metal belts 11 and 12 that rotates. A fixing tensioning device 13 equipped with left and right bolts 14, 15 that allows locking and a release device 1 assembled on the spacecraft.
6, and a bolt 17 at the free end, which is the other end of the metal belts 11, 12.

Both metal belts 11 and 12 have retaining rings formed at both ends thereof into which bolts 14, 15 and 17 are inserted. The fixed tension device 13 is the outermost solar panel 1 which is implicitly shown by laying the solar cells 19.
It is fixed to the frame number 8. Bolts 14, 15
is rotatable, so both bolts can push down the metal belts 11, 12. There is a distance of several cm between both metal belts 11 and 12.
Since the distance is maintained, the bolt 17 is rotatably pushed into the retaining ring at the lower end, which is the free end of both belts, so that the same distance is maintained at the lower end.

The release device 16 has a casing 20 with an opening 21 in which a piston 22 is supported.
The width of this casing 20 is the same as that of both metal belts 1.
It is necessary to select the casing 20 so that it fits between 1 and 12. The piston 22 has a recess 23 in which the bolt 17 can be locked. The housing 20 itself is provided with a side recess 24 into which the bolt 17, which is supported in the piston 22, can be inserted. Piston 22
The support rope 27 is connected via the rod 25 and the lever mechanism 26.
is connected to. Although not shown in detail, the support rope 27 is a component of a release mechanism that is known per se. The release mechanism includes a plurality of fasteners connected under tensile stress to the support ropes 27, and the solar panel can be released for deployment simply by loosening the support ropes 27. . Accordingly, the supporting cable can be cut by the ignition device at a predetermined point after the spacecraft is normally separated from the final stage rocket.

To install this device, first stack the solar panels on top of each other. Additionally, this solar panel is equipped with a device that provides an accordion-like crease. A stacked structure consisting of an arbitrary number of solar panels based on this idea is fixed to the wall of a spacecraft. Furthermore, the outermost solar panel 18
Unwind the pair of metal belts fixed to the bolt 1
7 to lock the recess 23 of the piston 22.
At this stage, the piston has been removed from the casing 20 and the support rope 27 is not under any tensile stress.

The piston 22 is inserted into the side recess 24 together with the bolt 17.
When the metal belts 11 and 12 are pushed into the casing 20 having the above-mentioned shape, the metal belts 11 and 12 cannot be removed upwardly. In this position, the piston 22 is stopped by a support rope 27. The metal belts 11, 12 are thus placed under a tensile stress of, for example, 200 kp by means of the fixed tensioning device 13. Since the above is done by rotating the bolts 14, 15, both metal belts are easily wound up. In this manner, individual solar panels are stacked on their frame or other mounting location and pressed toward the spacecraft.
Together with the flying object, this panel forms a compact unit that is insensitive to acceleration during launch.

The solar panel is released for deployment by loosening the support ropes 27, as described above. This loosening causes the lever mechanism 26 to move in the direction of the arrow. Since the side recess 24 inside the casing 20 is slightly inclined diagonally upward, the metal belt 1
This movement is further supported by the natural tendency of the bolt 17 to release due to the tensile stress of 1,12. The piston 22 moves forward,
Bolt 17 will come off. The metal belts 11 and 12 are
As shown by the dashed line, it rolls up to the outermost solar panel 18. Thus, the deployment of the solar panel progresses further.

Two or more fasteners are required per set of stacked structures, depending on their dimensions. For example, six fasteners are sufficient to construct a system with an end length of 3 m.

The material of the metal belts 11, 12 depends on the intended use. For spaceflight, beryllium-copper alloys have been proven to be able to be hardened well after forming. This system is suitable for extreme temperatures, e.g. -180°C to +120°C.
Suitable for temperatures up to °C, changes in length do not result in unacceptable changes in prestress.

[Brief explanation of drawings]

The accompanying drawings are perspective views of embodiments according to the invention. Reference symbols in the figure: 11, 12...Metal belt, 1
3... Fixed tension device, 16... Release device, 18...
...Solar panel, 28...Stacked structure.

Claims (1)

[Scope of Claims] 1. A fastener for a solar panel of a self-expandable spacecraft object folded into a stacked structure, wherein the fastener is a fastener installed in the frame of the outermost solar panel 18. A tension device 13;
A release device 16 installed on the spacecraft and one end rotatably attached to the fixed tension device 13 and the other free end attached to the fixed tension device 13 after release.
The bundle of the stacked structure consists of metal belts 11 and 12 having spring characteristics that allow the metal belts 11 and 12 to be wound up into a coil shape until the metal belts 11 and 1
The fastening is performed by locking the free ends of the metal belts 11 and 12 with a release device 16, and further applying tensile stress to the metal belts 11 and 12 after locking. 2. The metal belts 11 and 12 are arranged in pairs, and each pair 10 has a common bolt 17 for locking to a common release device 16, and this bolt 17 is inserted between the metal belts 11 and 12. 2. The fastener according to claim 1, wherein the fastener is partially engaged with the release device (16). 3 Fixing and tensioning device 1 for fixing the metal belts 11 and 12 of the pair 10 at the outermost solar panel 18
3. The fastener according to claim 2, wherein the fastener is fixed to the fastener 3 with left and right bolts 14, 15. 4. Any one of claims 1 to 3, wherein both ends of the metal belts 11, 12 are formed into retaining rings that slide along the surfaces of the bolts 14, 15, 17, respectively. Fasteners as described in paragraph 1. 5. The fastener according to claim 4, wherein the tension of the metal belt is applied by rotating bolts 14 and 15 at the outermost solar panel 18. 6. The release device 16 has a piston 22 supported in a cylinder 21 in a casing 20, and the piston 22 has a recess 23 for locking the bolt 17 of the metal belts 11, 12. There is a side recess 24 for locking the tightening bolt 17 of the stack structure 28, and a piston 22 for releasing this stack structure 28 is connected to the rod 2.
6. The fastener according to claim 5, wherein the fastener can be removed from the casing 20 by means of a lever mechanism 26, a lever mechanism 26, and a support rope 27. 7. The fastener according to claim 6, wherein the side recess 24 extends slightly diagonally upward within the casing 20. 8. The fastener according to claim 1, wherein the release device 16 is capable of simultaneously releasing the metal belts 11, 12 of the stacked structure 28 using a common support rope 27.