JPS6116200A - Power generator for artificial satellite - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION [Technical Field of the Invention] The present invention relates to a power generation device that obtains power for a satellite from sunlight.

[Prior art]

Figure 1 is a conceptual diagram of conventional power generation for spin satellites υ(
1) is a solar panel with solar cells attached to the outer surface of the satellite.

Conventional power generation by a solar cell panel (11), as shown in FIG. 2, is achieved by the power generated from the solar cell upon irradiation of parallel rays from the sun onto the solar cell panel.

However, as is clear from Figure 2, only the solar cells in the sunlight irradiated part of the solar panel (1) contribute to power generation, and about two-thirds of all solar cells are not constantly irradiated with sunlight. No electricity is generated from this part.

For this reason, when a large amount of electric power is required, it is necessary to increase the external size of the solar panel, increase the number of solar cells installed, and increase the number of solar cells in the solar irradiation area. However, even if the external size is increased, it is difficult to satisfy large power requirements.

[Summary of the invention]

This invention was made for the purpose of improving such drawbacks, and a solar reflecting plate is placed around the non-sunlit part of the solar panel, and the sunlight is reflected by the sunlight reflecting plate onto the non-sunlit part of the solar panel. This paper proposes a power generation device for a satellite that makes it possible to measure the increase in the generated power by reflecting it to the surface of the satellite.

[Embodiments of the invention]

FIG. 3 is a conceptual diagram showing one embodiment of this invention (1)
is exactly the same as the conventional device. (2,).

(2b) is two sunlight reflecting plates placed around the part of the solar panel (1) that is not irradiated with sunlight, and one reflective surface is made of a highly reflective material such as aluminum foil. .

(3,), (3b) are two solar reflectors (2a),
This is an arm that supports (2b). , (4) is a drive motor, and arms (3a) and (3b) are attached to the rotation axis of the motor.
is fixed, and the drive motor (4) rotates in the opposite direction to the rotation direction of the satellite.

(5) is a sun sensor that generates a signal when it detects the sun according to the rotation of the satellite.

Figure 5 is a block diagram showing the motor drive system (6
) is a tachogenerator (7) is a position sensor.

Both are attached to a drive motor (4). (8)
is the motor control circuit.

Arms (sa), (sb) and sunlight reflector (2a)
, (2b) is stored at the bottom of the satellite as shown in Figure 6.

First, deploy the arms (3a) # (3b), take out the solar reflectors (2a) and (2b) outside the satellite, and then deploy them.
The drive motor (4) is operated to rotate in the opposite direction to the rotation direction of the satellite.

In FIG. 5, the rotational speed of the satellite is obtained from the signal of the sun sensor (5) by a speed detector (9) which measures the repetition period of the sensor signal. On the other hand, the rotational speed of the drive motor is obtained from the tacho generator (6).

These two signals are compared and the motor drive circuit ←j operates the drive motor so that the error converges.

When the rotational speeds of the drive motor (4) and the satellite match, the sunlight reflecting plates (2a) and (2b) come to a so-called despin state where they stop in inertial space. In this state, the timing detection unit α2, which compares the solar sensor signal generation timing and the position sensor generation timing and generates an error signal, matches the generation timing of the solar sensor signal and the position sensor signal, and then moves the solar light reflecting plate (2a). t (2b) shown in FIG. 4 is directed toward the sun.

If the signal from the sun sensor (5) is missing, only the signals from the tachogenerator (6) and position sensor (7) will be input to the motor control circuit (8), and normal motor drive operation will not be maintained.

In this state, the motor control circuit (8) matches the rotational speed of the satellite and the drive motor to maintain the despin state.
The sun detection section, hold circuit αυ and relay (R1),
(R2) is placed. The contents of the speed detection section α2 are always held in a hold circuit (L+) and the value is updated every time a solar signal is detected.

Relay (R1) if the sun is not detected;
(R2) is operated to separate the signal from the timing detection section α, and the signal is compared between the satellite rotational speed information held in the hold circuit aυ and the tachogenerator (6), and the sunlight reflecting plate (2a), (2b) is maintain the despin state.

In the above embodiment, the sunlight reflecting plates (2a) and (2b)
Although the two-plate configuration was adopted, an increase in the generated power can be expected even with a solar reflector plate configured with either one of (2a) or (2c).

〔Effect of the invention〕

As described above, the present invention includes a solar reflecting plate having a simple structure arranged near a solar panel.

This has the effect of making it easier to increase power by reflecting sunlight on parts of the solar panel that are not exposed to sunlight and generating power from the solar cells in those parts.

[Brief explanation of the drawing]

Fig. 1 is a conceptual diagram of power generation by the solar panel of a conventional spin satellite, Fig. 2 is a diagram showing the sunlight irradiation area on the solar panel, and Fig. 3 is a conceptual diagram showing an embodiment of the present invention. , FIG. 4 is a diagram showing the sunlight irradiation area on the solar cell panel according to an embodiment of the present invention, FIG. 5 is a block diagram showing directivity control to the sunlight reflecting plate, and FIG. b) is a diagram showing the development of the arm and the solar reflector. In the figure, (1) is a solar panel, (2a), (
2b) is a sunlight reflector, (3a), (3b) is an arm, (4) is a drive motor, (5) is a sun sensor, (6
) is a tacho generator. (7) is a position sensor, (8) is a motor control circuit, (9)
is the speed detection section, (1 (I is the sun detection section, aυ is the hold circuit. α is the timing detection section, and the 0th floor is the motor drive circuit. (R1) and (R2) are the relays. Note that they are the same in Figure 9. Codes indicate the same or corresponding parts.

Claims (1)

[Claims] A solar panel attached to the outer surface of the cylindrical satellite;
A sunlight reflecting plate that has an unfolding mechanism and reflects sunlight toward the panel; an arm that supports the sunlight reflecting plate and has an unfolding mechanism; and a rotating shaft of a motor that drives the arm. 1. A power generation device for an artificial satellite, comprising: a drive motor to which an arm is fixed; a control circuit for operating the drive motor; and a solar sensor for detecting the direction of the sun.