JPS5932599A - Control system of attitude of stationary orbit 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 The present invention relates to an attitude control system for a three-axis stable geostationary orbit artificial satellite that flies entirely on a corrected orbit.

Conventionally, there has been an earth sensor that detects attitude angle errors around the roll and pitch axes as a pseudo error detector for a three-axis attitude control satellite in a geostationary orbit. Only the earth sensor is used as a sensor, while the attitude sensor for the zero-momentum type 3411 control satellite is the yaw I sensor instead of the earth sensor.
The RF sensor that detects the attitude angle error of IjlI rotation υ is (
There are many C who are scolded.

In either case, the shell control system depends on the attitude angle error detection accuracy of the earth sensor, but since the earth sensor detects the earth's infrared energy, it is more sensitive than solar and stellar sensors. Attitude angle error detection accuracy suffers.

This invention relies on the attitude angle error detection signal of the earth sensor to improve the three-axis cost effort and vljdll accuracy.

When the satellite is in sunlight on My geosynchronous orbit, the attitude angle error around the pitch axis is detected by the all-sun sensor, and the attitude angle error around the roll and yaw axes is detected by the fixed star sensor to perform three-axis attitude control. The attitude control system, which is a feature of the present invention, will be explained below with reference to the drawings.

Fig. 1 shows an embodiment of the present invention. ,
(9) is the earth sensor, Uα is the roll wheel, uiI
is the pitch wheel, (121 is the yaw wheel, (1
31 is a data processor including an arithmetic unit. Figure 2 is the first
It shows the flow of signals between the components shown in the figure.

Three-axis attitude control # Star attitude side [lI41 purpose is yaw axis +
31 point to the center of the earth and make the pitch @ (21 perpendicular to the orbital plane. Therefore, now the star sensor (4)
When the center direction of the star sensor (41's two-dimensional screen iC
Among the deviations from the center of the image of the roaring North Star, the deviation in the roll axis direction becomes an attitude angle error around the yaw axis, and the deviation in the yaw axis direction becomes an attitude angle error in the roll @1 turn p. The four solar sensors (51-(81) together cover the pitch axis of the satellite, and as long as the satellite is exposed to sunlight, any one of the solar sensors (51-(81) measures the direction of the sun. If the data processor (131) always calculates the position of the satellite on orbit and the position of the sun using all the calculators, the sun sensor (51 to (It can be determined by the total sun direction calculation set in 81-61. Therefore, the difference between the actually measured sun direction and the attitude angle around the pitch axis calculated in the calculator - the sun direction when there is no difference. is the attitude angle error around the pitch axis.The attitude angle error around the pitch axis of the earth sensor is used as it is to determine the position of the satellite during the day.

As described above, the attitude angle errors around the roll axis, pitch axis, and yaw axis are measured by the data processor uJ using the star sensor (4), the sun sensor (ri1 to (8)), and the earth sensor (9).
The roll wheel l+u can be calculated by measuring the angle in the air and removing this attitude angle error.

The pitch wheel (IIL) can be calculated in the signal sound data processor +13 that drives the yaw wheel.By rotating the wheel and generating torque using the drive signal calculated in this way, three-axis attitude control is possible. Become.

As described above, according to the present invention, the stellar sensor (4)
and a solar sensor (51 to 81 and a data processor including an arithmetic unit + 131') to detect attitude angle errors around the three axes when the satellite is in sunlight. Compared to (9), the target sensor (4) and the sun sensor (51 to (81) have better attitude angle error detection compatibility, so
It is possible to obtain even more attitude control than the conventional three-axis attitude control satellite that uses all terrestrial sensors.

In the example, the wheel configuration consists of three orthogonal wheels, but the same applies to configurations consisting of four or more wheels and wheel configurations in which one of the wheels has bias angular momentum (especially when the dominant control is used). It is something that can be done.

[Brief explanation of drawings]

Figure 1 shows the artificial dense layer of geostationary orbit according to the present invention, vj
In order to explain the IJ method, I used three-axis bite, 'bl+
Figure 2 is a diagram for explaining the connections and signal flow between the components of the Baud C in Figure 1.
1 is the roll ta, (2+ is the pitch axis, (31 is the yaw axis. (4) is the star sensor, (5) to (81 is the sun sensor,
(9) ￥i earth sensor, QUI is a roll wheel,
till is bifuchi j; eel, U21 is yaw wheel, Agent: Shin Kuzuno −

Claims (1)

[Scope of Claims] A stellar sensor that observes a star 'fc and detects an attitude angle error around the roll axis and yaw axis υ; a sun sensor that observes the sun and detects an attitude angle error around the pitch axis; A geostationary orbit that performs three-night attitude control using an earth sensor that observes the entire earth and detects attitude angle errors around the pitch axis, and a momentum wheel that generates rotational torque around the roll, pitch, and yaw axes. In the attitude control system of artificial satellites. Attitude angle error detection signal around the roll axis and yaw axis of the above-mentioned star sensor, attitude angle error detection signal around the pitch axis 9 of the above-mentioned sun sensor, and 2 When the artificial # star is in the 6th gap, around the pitch axis of the above-mentioned earth sensor. and the attitude angle error detection signal are input to the data processor. An attitude control system for a geostationary orbit artificial satellite, characterized in that the entire momentum wheel moves according to the output of a data processor to remove attitude errors around the roll axis, pitch axis, and yaw axis of the artificial satellite.