JPS61226396A - Solar sensor device - 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 three-wheeled attitude 1111 of an artificial satellite orbiting the earth.
This invention relates to a solar sensor device used in 0.

[Technical background of the invention and its problems] In general, an attitude detection device is required to perform three-wheel attitude control of an artificial satellite orbiting the earth. The present invention relates to a yaw attitude detection device using a sun sensor in this attitude detection device.

FIG. 2 shows a solar sensor device using a conventional method. That is, as shown in FIG. 2(a), the first solar detector 6, the second
The solar detector 7 is mounted on the solar panel 2 and the south panel 3, which are solar panels that rotate with respect to the Ifi star body 1. The first solar detector 6 is mounted in a mounting direction 9 inclined at an angle α with respect to the reference direction 11 by the first solar detector mounting base 4, and the second sun detector 7 is mounted in a mounting direction 9 tilted at an angle α with respect to the reference direction 11. Angle α with respect to the reference direction 11 by the detector mounting base 5
It is installed in the installation direction 10 inclined by 2.

Usually angles α1 and α2 are set to the same value. Then,
As shown in FIG. 2(b), the first solar detector 6, the second
The signal from the solar detector 7 passes through a slip ring 16 in the solar panel rotation drive device, and is converted from a current signal to a voltage signal 17°18 by a first buffer amplifier B12 and a second buffer amplifier 13, respectively. After being converted, the differential amplifier 14
to go into. The output attitude signal 15 of the differential amplifier 14 is the difference output between the intensity of sunlight incident on the first solar detector 6 and the intensity of sunlight incident on the second solar detector 7. Therefore, the second
As shown in Figure (C), this differential output attitude signal 15 has a characteristic proportional to the angle β formed between the sunlight direction 8 and the main body reference direction 11. This proportional area is 8
Considering the annual solar inclination angle between the plane and the geostationary orbit plane 2o, it was necessary to set it larger than ±23.5'.

In the solar sensor device configured as described above, since the first solar detector 6 and the second solar detector 7 are mounted apart from each other for use as a pair, the Different temperatures. Generally, solar detectors have characteristics that depend on the operating temperature, so the attitude signal 15, which is a differential output obtained from a pair of solar detectors with different temperatures, will have errors in its zero point and scale factor. There was a drawback. The same can be said about the temperatures of the first buffer amplifier 12 and second buffer amplifier 13 used in the first solar detector 6 and the second solar detector 7. .

A conventional solution to the above drawbacks is to attach two temperature control devices such as thermostats and heaters to the first solar detector mount 4 and the second solar detector mount 5, and install a pair of solar detectors 6 to 6. The aim was to eliminate the difference in density of .7. However, this measure has the drawbacks of increasing power consumption and deteriorating performance when the temperature control device fails.

[Object of the Invention] The present invention eliminates the above-mentioned drawbacks, and an object of the present invention is to provide a solar sensor device that can eliminate error factors associated with temperature fluctuations.

[Summary of the Invention] The solar sensor device of the present invention is a solar sensor device for detecting the attitude of an artificial satellite having a solar panel, in which a pair of solar detectors are mounted on the same mounting base on the solar panel. This is a characteristic feature.

[Embodiment of the Invention] An embodiment of the present invention will be described in detail below with reference to the drawings.

FIG. 1 shows an embodiment of the present invention, and the feature of the present invention is that as shown in FIG. 1(a), a first solar detector 20 and a second solar detector 21 used in a pair For example, among the solar battery panels that rotate with respect to the satellite main body 1, they are not mounted on the south panel 3, but are mounted all at once on the solar detector mount 19 on the north panel 2. . In this case, the first sun detector 20 is the sun sensor attitude reference 2
The second solar detector 21 is mounted in a mounting direction 22 tilted by an angle α1 with respect to the sun sensor attitude reference 25, and the second solar detector 21 is mounted in a mounting direction 23 tilted by an angle α2 with respect to the sun sensor attitude reference 25. The sunlight direction 8 is at an angle β with respect to the satellite body attitude reference 24.

As shown in FIG. 1(b), after the pair of solar detectors 20 and 21 are converted into differential outputs by the resistor network 26, the outputs of the solar detectors 20 and 21 are converted into differential outputs. jlN pond panel rotation drive! The signal is sent to the buffer amplifier 28 via the slip ring 27 in iI and becomes the attitude signal output 29.

As a result, since the temperature difference between the pair of solar detectors 20.21 is removed, the temperature difference between the pair of solar detectors J120.
It is possible to eliminate error factors such as the zero point of the differential output of No. 21. Furthermore, by generating the differential output of the pair of solar detectors 20,21 by means of a resistive network 26 installed on the solar detector mount 19, a buffer amplifier 28 is generated.
It is also possible to eliminate zero point errors due to temperature differences.

In addition, temperature control @1f30 is required to eliminate scale factor errors of the solar sensor device due to temperature fluctuations, but in this case, only one unit common to the pair of solar detectors 20 and 21 is required. , power consumption is also reduced.

[Effects of the Invention] As described above, according to the present invention, the zero point error of the solar sensor device against temperature fluctuations can be eliminated without using a concentration control device, and the zero point error of the solar sensor device against temperature fluctuations can be eliminated with fewer temperature control W devices. This has the advantage that scale factor errors in the solar sensor device can be eliminated.

[Brief explanation of drawings]

FIG. 1 is a configuration explanatory diagram showing one embodiment of the present invention, and FIG. 2 is a configuration explanatory diagram showing a conventional sun sensor device. 1...Main body, 2...North panel, 3...South panel,
19... Sun detector mounting base, 20... First solar detector, 21... Second solar detector, 26... Resistance network, 27... Slip ring, 28... ...Buffer amplifier, 30...Temperature control device. Applicant's agent Patent attorney Takehiko Suzue Figure 1 (a)

Claims (1)

[Claims] A solar sensor device for detecting the attitude of an artificial satellite having a solar panel, characterized in that a pair of sun detectors are mounted on the same mounting base on the solar panel.