JPS6238880Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Technical Field of the Invention] This invention relates to a solar array paddle deployment device mounted on an artificial satellite and converting solar energy into electrical energy.

[Technical background of the invention]

Conventionally, for example, solar battery paddles for power supply used in medium-sized or larger artificial satellites have been required to be large depending on the power used. For this reason, the paddles are folded during satellite launches.

That is, Figure 1a shows this state,
In the figure, 1 is the satellite body, 2 and 3 are inner panels that constitute paddles each equipped with a solar cell 4,
This is the outer panel. One end of the inner panel 2 is rotatably attached to the satellite body 1 by an inner hinge 5, and one end of the outer panel ₃ is rotatably attached to the other end of the inner panel 2 by outer hinges 61, ₆₂ . ing.

The inner hinge 5 and outer hinges 6 ₁ and 6 ₂
The paddle is equipped with a spring that provides the necessary deployment force to deploy the paddle, and a damper such as hydraulic pressure to control the speed at the time of deployment, that is, to reduce the impact at the end of deployment.

The paddle launched in the above state is deployed on the orbit as shown in FIGS. 1b and 1c, and the solar cells 4 provided on the inner panel 2 and outer panel 3 start generating electricity.

[Problems with background technology]

By the way, in the paddle mentioned above, a hydraulic damper is used to reduce the shock at the end of expansion, but this damper is prone to oil leakage in a thermal vacuum, and the leaked oil can damage the solar cells. They often pollute and cause a reduction in power generation, are large in size and heavy, and are highly affected by temperature changes, requiring a great deal of design effort and being very expensive.

[Purpose of invention]

This idea was made in order to eliminate the above-mentioned drawbacks of the conventional technology, and to create a low-cost solar battery paddle deployment device that does not cause paddle deployment to be affected by temperature changes and does not cause unnecessary shock to the satellite body. The purpose is to provide.

[Summary of the idea]

The solar battery paddle deployment device of this invention has a hinge section on each of the inner panel and outer panel constituting the paddle, these two hinge sections are connected by a spring, a friction load section is provided on the hinge section on the inner panel side, and a friction load section is provided on the hinge section on the outer panel side. A cam member having a long diameter part, for example, a deformed circle is provided in the hinge part of the cam member, and as the paddle is deployed, this deformed circle increases the frictional force with the frictional load, so that the impact when the paddle is deployed is absorbed by this frictional load part. It is.

[Example of idea]

Embodiments of the solar cell paddle deploying device of this invention will be described below based on the drawings. 2a to 2d show the hinge portion in each embodiment, FIG. 2a shows the state before deployment, FIG. 2b shows the state after deployment, and further,
FIG. 2c is a bottom view of FIG. 2b, and FIG. 2d is an enlarged bottom view of the friction load portion of the outer hinge.

2a to 2d, the hinge part 13 on the inner panel 12 side has a case 14a, a spring 14b, and a contact rod 14c as shown in FIG. 2d.
A friction load section 14 consisting of the following is provided. That is, a coiled spring 14b is housed in the case 14a, and this spring 14b
is in contact with one end of the contact rod 14c. The other end of the contact rod 14c is in contact with the outer peripheral surface of a cam member having a long diameter portion, for example, a deformed circle 15 which is an eccentric portion to be described later.

On the other hand, 16 is an outer panel, and 17 is a hinge portion on the outer panel 16 side. As the hinge portion 17 on the outer panel 16 side unfolds, a deformed circle 15 is provided such that the distance between the center of rotation between the hinge portions and the contact rod 14 (FIG. 2 d) increases, and as shown in FIG. 2 b. As shown, one end of the sprig 18 is fixed to the hinge part 13 on the inner panel 12 side, and the other end is fixed to the hinge part 17 on the outer panel 16 side.

Next, the operation of the solar cell paddle deploying device of this invention constructed as described above will be described. At the time of satellite launch, the inner panel 12 and outer panel 16 are folded into the state shown in FIG. 2a.
When the paddle is deployed, it is rotated in the direction of arrow B shown in FIG. 2A by a spring 18 provided on the hinge portion 17 on the outer panel 16 side.

In this rotating state, the hinge portion 17 rotates and at the same time the deformation circle 15 provided on the hinge portion 17
rotates around point A of the hinge portion 17. As this deformed circle 15 rotates, the contact rod 14c provided on the hinge part 13 is gradually pressed, and the pressure of the spring 14b causes the deformed circle 15 to rotate.
The frictional force between the contact rod 14c and the contact rod 14c increases, and it is possible to easily suppress the impact when the paddle is deployed, and it is possible to eliminate the adverse effects of impact on the satellite body.

Note that the above explanation applies to the outer hinge 6 in FIG.
Although only the inner hinges ₁ and ₆₂ have been described, the same applies to the inner hinge 5 in FIG.

[Effect of idea]

As described above, according to the solar battery paddle deployment device of this invention, the inner panel and the outer panel constituting the paddle are each provided with a hinge part, these two hinge parts are connected by a spring, and the hinge part on the inner panel side is connected with a spring. A friction load section is provided, and a deformation circle is provided on the hinge section on the outer panel side, and as the paddle is deployed, this deformation circle increases the frictional force, and the impact when the paddle is deployed is absorbed by this friction load section, so that temperature changes can be avoided. Uncertainty factors such as
In addition, there is no need to worry about oil leakage, and the impact force at the end of deployment is reduced.

[Brief explanation of the drawing]

Fig. 1a is a perspective view showing a conventional solar cell paddle in a folded state, Fig. 1b and Fig. 1c are views each showing a conventional solar cell paddle in an unfolded state, and Fig. 2a is a perspective view of the conventional solar cell paddle in a folded state. FIG. 2b is a bottom view showing the state of the hinge section of an embodiment of the solar battery paddle deployment device before deployment, FIG. 2b is a side view showing the state of the hinge section after deployment, and FIG. Bottom view, 2nd
Figure d is an enlarged bottom view of the friction load section in the hinge section. 12... Inner panel, 13, 17... Hinge part, 14... Friction load part, 14a... Case, 1
4b, 18... Spring, 14c... Contact rod,
15... Deformed circle, 16... Outer panel.

Claims (1)

[Scope of utility model registration request] A plurality of panels each constituting a solar array paddle, a hinge portion equipped with a spring that applies an unfolding force to bring adjacent panels of the plurality of panels from a folded state to an unfolded state, and this hinge portion. a cam member provided on one panel coaxially with the axis of the panel, and a friction load section provided on the other adjacent panel of the panels so as to contact the cam member with a spring; A solar cell characterized in that the frictional load portion is provided such that the distance between the center of rotation of the cam member and the contact position of the frictional load portion with the cam member is approximately maximum when the adjacent panels are in an expanded state. Paddle deployment device.