JPH05213288A - Solar battery paddle system for space navigating body - Google Patents

Abstract

PURPOSE:To check the generated electric power of a solar battery paddle loaded on a space navigating body to fixed value. CONSTITUTION:Generated electric power monitor 4 monitors the generated electric power of a solar battery paddle 1, and sends the data to a paddle directivity angle setting device 3, which determines the turning angle theta of the solar battery paddle 1 necessary for keeping the generated electric power of the solar battery paddle 1 constant, and sends the value to a paddle driving device 2. The solar battery paddle 1 is rotated as much as the angle theta around a Z axis as a central axis to keep the generated electric power constant.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a solar cell paddle system for a spacecraft, and more particularly to a solar cell paddle system for a spacecraft having a sun tracking function in a geostationary orbit.

[0002]

2. Description of the Related Art Conventionally, this type of solar cell paddle system rotates about one axis with respect to the main body of the spacecraft and is controlled so that the incident angle of sunlight is always minimized.

[0003]

The conventional solar cell paddle system described above is controlled so that the incident angle of sunlight is always minimized. However, on a geosynchronous orbit, due to seasonal variations, the minimum incident angle of sunlight is minimized. Fluctuates greatly from −23.5 ° to + 23.5 °, and the solar cell paddle system generated power also increases or decreases accordingly.

For example, in the spring and autumn equinox, the incident angle of sunlight is 0 °, and the summer solstice and winter solstice are ± 23.5 °. Is 1.09 times.

Further, due to the deterioration of the conversion efficiency of the solar cell due to the radiation on the orbit, the power generation ratio at the beginning and the end of the mission becomes 1.19 times for a three-year mission, for example.

Since the solar cell paddle system is designed to supply the required electric power when the generated electric power is minimum in consideration of the generated electric power fluctuation, the generated electric power fluctuation causes generation of electric power exceeding the required electric power. At this time, the surplus power is absorbed by the shunt circuit, and a constant power is always supplied.

In the case of the solar cell paddle system of 5 kW class, the maximum surplus power is 6485 W (5
000 × 1.09 × 1.19) and generated power minimum value 500
The difference from 0 W is 1458 W, and the shape of the shunt circuit is determined correspondingly, and there is a drawback that it becomes large and heavy.

It is an object of the present invention to provide a solar cell paddle system for a spacecraft in which the above-mentioned drawbacks are eliminated, the surplus power generation amount is significantly suppressed, and the shunt circuit is remarkably lightweight.

[0009]

A solar cell paddle system for a spacecraft according to the present invention is a solar cell paddle mounted on a spacecraft, and the solar cell paddle is rotated about a predetermined axis to set an arbitrary angle. A paddle drive device for directing, a paddle directivity angle setting device for setting the directivity angle of the solar battery paddle by the paddle drive device based on the generated power of the solar battery paddle, and monitoring the generated power of the solar battery paddle. And a generated power monitor for supplying to the paddle directivity angle setting device.

[0010]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Next, the present invention will be described with reference to the drawings.

FIG. 1 is a block diagram of an embodiment of the present invention,
FIG. 2 is a conceptual diagram of the present invention.

The configuration of the embodiment shown in FIG. 1 has a solar cell paddle 1, a paddle drive device 2 for rotationally driving the solar cell paddle 1 around one axis, and a paddle orientation for setting a rotational orbit angle by the paddle drive device 2. Angle setting device 3 and solar paddle 1
And a generated power monitor 4 for monitoring the generated power.

Next, the operation of this embodiment will be described.

In FIG. 2, the solar cell paddle 1 can be oriented in any direction around the Z axis which is perpendicular to the X axis and the Y axis.

In the conventional solar cell paddle, as shown in FIG.
As shown in, the direction vector u of the sunlight is directed so as to be parallel to the plane formed by the normal vector of the cell array surface of the solar cell paddle and the solar cell paddle rotation axis, that is, the YZ plane.

On the other hand, as shown in FIG. 2 (b), when the solar cell paddle is rotated by an angle θ from the state of FIG. 2 (a), the solar cell paddle generated power is in the state of FIG. 2 (a). Cos θ times. In this solar cell paddle system, the generated power is controlled by utilizing this relationship.

That is, the generated power in the state of FIG.
When the required power is K times (K ≧ 1), the generated power can be adjusted to 1 / K, that is, just the required power by rotating the solar array paddle by the angle θ1 = cos ⁻¹ · 1 / K. it can.

In the present solar cell paddle system, the paddle directivity angle setting device 3 determines an appropriate directivity angle θ based on the generated power value obtained by the generated power monitor 4, and the paddle drive device 2 sets the solar cell paddle 1 to θ. By rotating, a predetermined generated power is obtained.

For example, by performing this angle adjustment twice a month, the maximum power generated by the solar cell paddle system can be suppressed to about 1.02 times the required power. On the other hand, in the conventional solar cell paddle system, 1.09 × 1.
19 = 1.30 times. When this is calculated in the case of a 5 KW class solar cell paddle system, the surplus generated power of the difference between the maximum generated power and the required power is 1485 W in the conventional solar cell paddle system and 100 W in the present solar cell paddle system. Becomes

The paddle pointing angle setting device 3 may not be mounted on the spacecraft, but may be installed in the operation facility of the spacecraft on the ground.

[0021]

As described above, according to the present invention, the generated power can be controlled by controlling the directivity angle of the solar cell paddle, and the surplus generated power is suppressed to a small amount to consume the surplus generated power. The shunt circuit has a small size and a light weight, and it is advantageous in terms of thermal design.

[Brief description of drawings]

FIG. 1 is a block diagram of an embodiment of the present invention.

FIG. 2 is a conceptual diagram of the present invention.

[Explanation of symbols]

 1 Solar cell paddle 2 Paddle drive device 3 Paddle directivity angle setting device 4 Generated power monitor

Claims (1)

[Claims] 1. A solar cell paddle to be mounted on a spacecraft, a paddle drive device for orbiting the solar cell paddle about a predetermined axis to direct an arbitrary angle, and a solar cell paddle by the paddle drive device. A paddle directivity angle setting device that sets a directivity angle based on the generated power of the solar cell paddle, and a generated power monitor that monitors the generated power of the solar cell paddle and supplies it to the paddle directivity angle setting device. A solar paddle system for spacecraft characterized by the following: