JPS60189696A - Controller for attitude of 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 an attitude control device for a three-axis stable artificial satellite flying in a geostationary orbit.

[Prior art]

FIG. 1 is a diagram for explaining a conventional attitude control device. In FIG. 1, (1) is an earth sensor that detects attitude angle errors around the roll axis and the pitch axis.

(2) is a solar sensor, (3) is a star sensor, (4) is an RF sensor that measures the direction of radio waves emitted from the ground, and (2) to (4) are attitude angle errors around the yaw axis. It is a device for detection. (5) is an artificial satellite, (6) is a geostationary orbit, (7) is the earth, and (8) is the sun. However, the solar sensor (2) has the disadvantage that it cannot detect attitude angle errors along the yaw axis when the sun (8), the earth (7), and the satellite (5) are aligned on a straight line. . Stellar sensor (
In the case of 3), the equipment is complicated and expensive, and the star observed within the field of view of the star sensor is fixed in that it corresponds to a star in the star catalog whose right ascension and declination are known in advance. It has the disadvantage that it requires some processing. In the case of an RF sensor (4) that measures all directions of radio waves emitted from the ground, the output signal indicates the attitude angle error itself around the yaw axis, and has a complex relationship with the attitude angle error around the roll and pitch axes. [Summary of the Invention] This invention was made to improve all of the above-mentioned drawbacks of the conventional technology, and the yaw axis load is low. In order to constantly measure the relative attitude angle error with high precision regardless of the satellite's position, and without complex data processing, an optical sensor mounted on the first satellite in geostationary orbit is used as a sensor on the second satellite in geosynchronous orbit. Artificial? Mounted on the l1IJ star, it also observes the sunlight emitted by the solar reflector to detect all attitude angle errors in the yaw axis, and uses an earth sensor to detect attitude angle errors in the roll and pitch axes. It is designed to detect and perform three-axis attitude control. In addition.

It is assumed that the second artificial satellite is flying completely in the vicinity of the artificial satellite on the geostationary orbit, which originally performs three-axis attitude control.

[Embodiments of the invention]

DESCRIPTION OF THE PREFERRED EMBODIMENTS An attitude control device that is a feature of the present invention will be described below with reference to the drawings.

Figures 2 and 3 show one embodiment of this invention.9
In the figure, (1) is the earth sensor, (5a) and (5b) are the first and second artificial satellites in geosynchronous orbit, (6) is in geosynchronous orbit, (7) is the earth, (9) is the roll axis, and a ■ is the pitch axis.

01) is the yaw axis, 021 is the roll wheel, 03) is the pitch wheel, 041 is the yaw wheel, 051 is the data processor including arithmetic unit, 06) is the optical sensor, 071
is a solar reflector. FIG. 3 shows the flow of signals between the components shown in FIG.

The purpose of attitude control for a three-axis attitude control satellite is to orient the yaw axis (01) to the center of the earth and the pitch axis (101i) perpendicular to the orbital plane.
The first artificial satellite (5b) is flying close to the first artificial satellite (5a) on its original geostationary orbit.

On the second artificial satellite (5b) on the geosynchronous orbit, change the direction of sunlight reflected by the solar reflector around the positive or negative roll axis direction to the original first artificial satellite (5a) on the geosynchronous orbit. When the satellite sensor (1G+) installed in
-5a) shows the total attitude angle error around the yaw axis α1).

When the second artificial satellite (5b) on the geosynchronous orbit is away from the equatorial plane, the amount of separation is calculated on the ground and input to the data processor Q51, and the output signal of the optical sensor (flit) is given a bias amount. 7 yaw axis Q11 by adding as
A signal indicating the attitude angle error of the surroundings is obtained. Roll axis (
9) and the pitch axis (1014) attitude angle error is indicated by the output signal of the earth sensor (1).

As described above, by performing correction calculations in the data processor Q51 if necessary, the output of the optical sensor (161° earth sensor (1)) is adjusted to the roll axis (9) and pitch axis QOI.
and yaw fgll' (111-f) and the attitude angle error of 111-f. By rotating the wheel and generating torque, three-axis attitude control becomes possible.

[Effects of the invention] 1. As stated above, this invention has the advantage that
■By using a satellite, an optical sensor, an earth sensor, and a data processor including a computing unit.

It is possible to detect attitude angle errors around the three axes of the satellite, especially when detecting all attitude angle errors due to the weight on the yaw axis.
Compared to conventional three-axis attitude control satellites that use solar sensors, fixed star sensors, and RF sensors that measure all directions of radio waves emitted from the ground, this satellite can always control its attitude regardless of the satellite's position, and with simple data processing. It becomes possible to perform good posture control at all times.

In the embodiment, the wheel configuration consists of three orthogonal wheels, but the same applies to a configuration consisting of four or more wheels and a wheel configuration in which one of the plurality of wheels has bias angular momentum.

It is possible to control the posture.　′

[Brief explanation of the drawing]

FIG. 1 is a diagram for explaining the entire conventional attitude control device for an artificial satellite, and FIGS. 2 and 3 are diagrams for explaining the attitude control device for an artificial satellite according to the present invention. FIG. 4 is a diagram showing connections and signal flows between the disaster-prone devices shown in FIG. 3. In the figure, (I) is a solar sensor, (2) is a solar sensor, and (3) is a solar sensor.
) is a stellar sensor, (4) is an RF sensor, and (5) is an artificial satellite. (5a) is the first artificial satellite, (51)) is the second artificial satellite, (6) is in geostationary orbit, (7) is the earth, (8) is the sun,
(9) is the roll axis, u (g) is the pitch axis, (11+ is the yaw axis, t+z is the roll wheel, u31 is the pitch wheel, 0 (a) is the yaw wheel, 051 is the data processor, α61 is the optical sensor, Anh is a solar reflector.In addition, parts corresponding to bMk that are the same in Figure 1 are indicated by the same symbols. Agent Masuo Oiwa 1 Figure 2 Figure 3 Figure 4

Claims (1)

[Claims] An optical sensor that measures the direction of sunlight reflected by a solar reflector mounted on an artificial satellite in a geostationary orbit, and an optical sensor that measures the direction of sunlight reflected by a solar reflector mounted on an artificial satellite in a geosynchronous orbit, and an optical sensor that observes the earth and determines attitude angle errors around the roll and pitch axes. Earth sensor to detect and roll axis. A wheel that generates all rotational torque around the pitch axis and yaw axis, an attitude angle error detection signal around the yaw axis of the optical sensor, and an attitude angle error detection signal around the roll axis and pitch axis of the earth sensor. It is characterized by being fully equipped with a processor that creates a signal for eliminating stability errors due to the roll, pitch, and yaw axes of the satellite based on the satellite, and drives the wheel using the signal. Attitude control device for artificial satellites.