JPS5933760Y2 - solar paddle - Google Patents

Description

[Detailed Description of the Invention] This invention relates to an improvement of a solar array paddle used in, for example, a three-axis attitude stabilization type artificial satellite.

As is well known, for example, in a three-axis attitude stabilization type artificial satellite, in order to improve power efficiency, a solar battery paddle 12 provided with a plurality of solar battery elements 11 is often used as shown in FIG. 1 aeb.

This solar battery paddle 12 is rotationally controlled relative to the satellite body 13 so as to track the sun, but since this tracking is usually -axis tracking, it is often tilted with respect to other axes.

Generally, the efficiency η of the solar cell element 11 is η(xmsjnθ Therefore, it is desirable that θ be close to 900.

Therefore, it is conceivable to tilt the paddle 12 with respect to the satellite body 13 as shown in FIG.

However, with this structure, as the paddle 12 rotates, the product of inertia (particularly in the XZ direction and YZ direction) among the mass characteristics of the satellite body 13 increases, and the disturbance torque (accumulation) applied to the satellite body 13 increases. .

Therefore, propellant is wasted to offset the disturbance torque, which ultimately shortens the life of the satellite.

In order to avoid this, the structure shown in FIG. 3 can be considered.

That is, FIG. 3 attempts to suppress an increase in the product of inertia by making the center of the solar cell paddle 12 the center of rotation.

Incidentally, the solar battery paddle 12 is folded when the satellite is launched, and is expanded when the satellite enters a predetermined orbit.

For this reason, it is necessary to test the paddle deployment on the ground, but it is difficult to perform the test with the paddle structure shown in FIG.

That is, if the expansion can be carried out in two dimensions, the paddle 12 is placed on the surface plate 14 as shown in FIG. By doing so, it is possible to simulate paddle deployment in a zero-G field.

However, in the case of the paddle shown in FIG. 3, it is difficult to fold the paddle 12 in a certain direction.

For this purpose, the paddle 12 is folded so as to wrap around the satellite 13, for example.

Therefore, since the direction of expansion is three-dimensional, it is difficult to perform a comprehensive simulation of expansion using the method described above, and there is a problem in terms of reliability.

This idea was made based on the above circumstances, and it makes the center of gravity of the solar array paddle coincide with the center of rotation of the paddle rotation axis, and allows the paddle to be folded and unfolded in two dimensions, extending the life of the satellite. It is an object of the present invention to provide a solar cell paddle that can improve the reliability of paddle deployment.

An embodiment of this invention will be described below with reference to the drawings.

In FIG. 5a, 21 is a satellite body, and this satellite body 21 is provided with, for example, an L-shaped support shaft 22 whose rotation is controlled according to the direction of the sun.

This support shaft 22 has one end 231 of the solar cell paddle 23.
is rotatably provided.

The other end portion 232 of this solar cell paddle 23 is connected to the intermediate portion 23.
It is said that it is possible to rotate.

In the above configuration, when the satellite is launched, the solar battery paddle 2
One end portion 230 and the middle portion 233 of 3 are folded in a certain direction, resulting in the state shown in FIG. 5.

When the satellite enters a predetermined orbit, the solar array paddle 23 is moved using a spring or the like (not shown) as shown in FIG.
It is expanded to the state shown in .

In this unfolded state, the solar cell paddle 23 is tilted at a predetermined angle with respect to the support shaft so that the incident angle of sunlight is approximately 900 degrees.

Further, the length and inclination angle of the paddle 23 are determined so that the center of gravity of the solar cell paddle 23 coincides with the rotation center of the support shaft 22 in this state.

According to the above configuration, the center of gravity of the solar battery paddle 23 and the support shaft 2
The rotation centers of 2 are made to coincide.

Therefore, it is possible to suppress an increase in the product of inertia exerted on the satellite 21 due to the rotation of the paddle 23, and the consumption of propellant for offsetting disturbance torque can be reduced, so that the life of the satellite can be extended.

Furthermore, since the paddle 23 is deployed in one step and in two dimensions in a fixed direction, it is possible to easily conduct a deployment test on the ground, and reliability can be improved.

Furthermore, since the paddles are tilted at a predetermined angle in the direction of sunlight in the unfolded state, it is possible to improve power efficiency.

Note that this invention is not limited to the above embodiments,
For example, the configurations shown in FIGS. 6a, b, and c can also provide the same effects as in the embodiment described above.

However, in FIGS. 6a, b, and c', the same parts as in FIG. 5 are given the same reference numerals.

As detailed above, according to this invention, the center of gravity of the solar array paddle coincides with the center of rotation of the paddle rotation axis, and the paddle can be folded and unfolded in two dimensions, extending the life of the satellite. Accordingly, it is possible to provide a solar cell paddle that can improve the reliability of paddle deployment.

[Brief explanation of drawings]

Figures 1a, b to 3 are configuration diagrams showing different conventional solar array paddles, Figure 4 is a diagram for explaining a solar array deployment test, and Figure 5a is a diagram showing the structure of the solar array paddle according to this invention. A schematic configuration diagram showing one embodiment of a solar battery paddle, a schematic configuration diagram showing a state different from that shown in FIG. 6a, FIG. 6a,
b and c are schematic configuration diagrams showing other embodiments of this invention, respectively. 21...Satellite main body, 22...Rotation axis,
23...Solar battery paddle.

Claims (1)

[Scope of utility model registration request] A support shaft that is provided on the satellite body and whose rotation is controlled according to the direction of the sun, and one end of which is provided on the support shaft so that it is deployed in a fixed direction and whose center of gravity coincides with the center of rotation of the support shaft in the deployed state. Solar cell paddle 0 characterized by being provided at an angle