JPS58145599A - 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 The present invention relates to an attitude control device mounted on an artificial satellite, and more particularly to an attitude control device that makes the operation of a satellite's mission equipment more efficient.

As an example of mission equipment mounted on a satellite.

There are sensors such as infrared radiometers for observing the earth, but in satellites orbiting the earth at medium and low altitudes, these sensors acquire data every orbit. In this case, it is necessary to obtain valid data so that there are no duplications or omissions in the locations where data is obtained every nine laps. Conventionally, as an example of a method for obtaining valid data, there is a method of precisely controlling the orbit of a satellite around the earth.

Specifically, the orbit of the satellite is calculated on the ground.

A method has been adopted in which the semi-major axis and the orbital inclination of the orbit of a satellite around the earth are controlled by thrusters to set the satellite in a predetermined orbit. However, this method requires calculation of complex satellite orbits on the ground and requires a large amount of thruster propellant. In addition, there was a limit to the accuracy of orbit control due to the feasibility of achieving higher accuracy in orbit calculations on the ground.

Furthermore, as another example of a conventional method, a device has been considered that obtains effective data by pointing a sensor in the direction in which data is desired to be obtained. Figure 1 shows the principle diagram. In meat (11 is an artificial satellite in orbit, (2
+L)Fi Mission equipment not facing the desired direction,
(2b) shows the mission equipment facing the desired direction, (3a) shows the location where data is acquired by the mission equipment not facing the desired direction, and (3b) shows the location where the data is desired to be acquired. As is clear from the figure, from the orbit of the satellite (11), the mission equipment (2a)
The location (6a) from which data is acquired may not be the desired location (3b) due to a shift in the orbit of the satellite. In that case, if the mission device (2a) is moved so as to direct the mission device (2b) to the desired location (6b), it becomes necessary to acquire more effective data.

However, this method requires a mechanism (such as a gimbal mechanism) for moving the mission equipment and a drive circuit thereof, making the mission equipment complicated. Moreover, if the movable parts become large, it is difficult to realize such a single device.

This invention solves the shortcomings of the conventional methods as described above, and by controlling the satellite, it directs the mission equipment in the desired direction and acquires valid data. There is also no problem with the amount of thruster propellant, and there is no need to complicate mission equipment such as having moving parts.

The present invention will be explained below with reference to the drawings. FIG. 2 is a detailed explanation of the present invention, and the same parts as in FIG. 1 are designated by the same reference numerals.

As is clear from the figure, by controlling the satellite ill in orbit (controlling the artificial satellite (1) to the position indicated by the broken line in the figure), the mission equipment (2a) can be moved from the orbit of the satellite (11).
The location (5a) from which data is acquired is the desired location (3b)
If not, move the mission equipment (2a) to the desired location (6
b).

FIG. 3 is an explanatory diagram showing one embodiment of the present invention.

In the figure, (4) is a sensor that detects the attitude of the satellite.

(5) is a controller that processes the attitude control law of the satellite.

(6) is an actuator that moves the attitude of the satellite, and (7) is a signal generator that directs the satellite in a desired direction.

(8) indicates an adder.

Normally, the attitude of the satellite is detected by a sensor (4), the detected signal is processed by a controller (5), and the processed signal drives an actuator to move the two artificial satellites. Through this series of processing, the satellite is controlled in the direction of the earth, etc. In the case of Earth View 111 II satellite etc.
An earth sensor or the like is used as a sensor, and the two artificial satellites are controlled to face the center of the earth. In such a satellite attitude control device, in order to direct the mission equipment to the desired location as shown in Figure 1, the mission equipment (2a) must be oriented in the desired direction in Figure 1. Location (5) where data is acquired by mission equipment (2a)
PL) to the desired position (5b). To that end, in Figure 2,
A signal generator (7) K generates a signal suitable for achieving that state.
Therefore, the signal of the sensor (4) and the adder (8) K are added, and the controller (5) and the actuator (
6) The satellite can be controlled using K. The appropriate signal described above may be set by a command from the ground, or if known in advance, the content of the signal may be set in advance.

As explained above, by providing the attitude control device with a signal generator and an adder, it is possible to easily move the mission equipment in the desired direction without having to perform precise trajectory control or providing the mission equipment with movable parts. It turns out that it is possible to direct.

It should be noted that what is shown in FIG. 3 is one embodiment, and the present invention is not limited to the above-mentioned embodiment.
It is applicable to all attitude control devices for artificial satellites that have mission equipment.

[Brief explanation of the drawing]

FIG. 1 is a diagram showing the principle of an example of a conventional attitude control device, FIG. 2 is a diagram of the principle of using the attitude control device according to the present invention, and FIG. 3 is a diagram showing an embodiment of the present invention. be. In the figure (11 is the artificial satellite, (2a) and (2b) are the mission equipment mounted on the artificial satellite, (5a) and (6b) are the locations where the mission equipment acquires data, (
4) is a sensor, (5) is a controller, (6) is an actuator, (7) is a signal generator, and (8) is an adder. In Figure 1, partial pressures corresponding to the same pressure are indicated by the same symbols. Agent Makoto Kuzuno - Figure 1 Figure 2 J (1:jb

Claims (1)

[Claims] In the attitude control device for an artificial satellite, when the mission equipment of one artificial satellite deviates from the desired direction due to a deviation in the orbit in the observation direction. It has a signal generation circuit to correct the deviation. An attitude of an artificial satellite, characterized in that the attitude of the artificial satellite is controlled based on the output of the signal generation circuit and the output of an attitude sensor of the artificial satellite, and the mission equipment is directed in a desired direction. Control device.