JPS60197498A - Controller for orbit 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 orbit control device for a three-axis stable artificial satellite flying in a geostationary orbit.

[Prior art]

Conventional orbit inclination control of this type involves determining the orbit of one artificial satellite at a ground station, and transmitting the thruster injection start time and injection time from the ground station to the satellite based on the control date and time and control amount estimated from the determined value. This was carried out by firing thrusters according to commands. Therefore, a large amount of work such as orbit determination before control, creation of control commands, command transmission, orbit determination after control, and prediction of the next control timing based on the determined values must be performed at the ground station during the satellite operation period. There was a drawback that it was not possible.

[Summary of the invention]

This invention was made with the aim of improving such drawbacks, and by equipping a satellite with a stellar sensor (hereinafter referred to as the Volaris sensor) that observes the North Star and a device that processes this sensor data, there is no need for instructions from a single ground station. This project proposes an orbit control device for artificial satellites that controls the orbital inclination angle onboard.

[Embodiments of the invention]

1 and 2 show a schematic diagram of an artificial satellite on a geostationary orbit and components on the satellite body for explaining the present invention. In the figure, (1) is the earth, +2) is the satellite's orbit, (3) is the equatorial plane, (4a) is the satellite when it passes a diplomatic point, and (4b) is when it is farthest north from the equatorial plane. satellite, (4c) is the satellite when passing through the descending node, (
4a) is the satellite when it is farthest south from the equatorial plane.

(5) is the orbital inclination angle, (6) is the thruster attached to the one pitch axis side, (7) is the thruster attached to the top pitch axis side, (8) is the roll axis, (9) is the pitch axis, G[l is the yaw axis.

(11a) is a data processor 1 that determines the position of the North Star on the Volaris sensor coordinates, and (11b) is a data processor that selects an injection thruster from the position of the North Star determined in (11a) and creates a signal instructing execution of injection. vessel 2, ti
2 is a volaris sensor. Figure 3 shows the position of Polaris on the Volaris sensor coordinates. In the figure, ti,
041, 0M, (te are (4a) in FIG. 1, respectively.

This is the position of the North Star on the Volaris sensor coordinates when the satellite is located at (4b), (4c), and (4a). Fourth
The figure shows the flow of signals between the components shown in FIG.

The attitude of the three-axis attitude control satellite is always controlled so that the yaw axis u1 is directed toward the center of the earth and the pitch axis (9) is perpendicular to the orbital plane. Therefore, if a volaris sensor is installed in one pitch axis direction of the satellite to be able to detect the Polaris, if the orbital inclination is 0 degrees, the center of the volaris sensor as shown in Figure 3, that is, both the roll axis direction and the yaw axis direction, will be zero. You will sense the North Star in your position. However, the first
If there is an orbital inclination angle (5) as shown in Figures and Figure 3.

Depending on the position of the orbit, the position at which the North Star is detected will rotate once per orbit. Using this, data processor 1
(11a) sends data on the position of the North Star on the Volaris sensor coordinates to the data processor 2 (1lb),
When the data exists in the area from 00 clockwise in Figure 3 to I passing through a axis, a signal is generated to fire the thruster (6) on the one pitch axis side, and from 04 clockwise a! When existing in the area from 9 to Oe, the thruster on the + pitch axis side (
7) Create a signal to inject and send that signal to the thruster to drive the thruster and bring the orbital inclination angle closer to zero. After the temperature reaches zero, the Volaris sensor detects the Polaris and fires the thrusters in accordance with the signal created by processing that data. After the firing, the Volaris sensor detects the data. By continuing to fire the thrusters at a cycle, the orbit is tilted. The angle will be held at approximately zero degrees. However, the smaller the thrust level of the thruster, the smaller the orbital inclination angle maintained. Also, the thruster 161. If the +71 cannot be installed parallel to the pitch axis so as not to generate torque, install two or more thrusters in each of the -pitch axis and +pitch axis directions, and the combined thrust vector will generate torque. It is only necessary to attach the thrust force in the translational direction so that it can be sufficiently controlled by the attitude control system even if no thrust force is generated.

[Effects of the Invention] As described above, according to the present invention, the orbital inclination angle of a satellite in a geostationary orbit can be maintained near zero degrees by the Volaris sensor and the data processor 1 that determines the position of the North Star on the Volaris sensor coordinates. Orbit inclination angle control is possible without sending control commands from the ground station by using the data processor 2, which selects the injection thruster from the North Star position on the Volaris sensor and creates a signal to instruct the start of injection execution, and the thruster. becomes.

[Brief explanation of the drawing]

Figure 1 is a diagram for explaining the position of an artificial satellite on its orbit and the direction of each axis, Figure 2 is a diagram for explaining the orbit control device for an artificial satellite according to the present invention, and Figure 3 is a diagram for explaining the satellite in orbit. FIG. 4 is a diagram showing the connection and signal flow between the components shown in FIG. 2. In the diagram, (1) is the earth, (2) is the orbit of the satellite, and (3)
is the equatorial plane, (4a) is the satellite when passing the diplomatic point,
(4b) is the satellite when it is farthest north from the equatorial plane, (
4c) is the satellite when it passes through the descending node, (4a) is the satellite when it is farthest south from the equatorial plane, (5) is the orbital inclination, (6) is the thruster attached to the -pitch axis side, ( 7)
is the thruster attached to the +pitch axis side, (8) is the roll axis, (9) is the pitch axis, Ql is the yaw axis, (11a)
(11b) is a data processor 1 that determines the position of the North Star on the Volaris sensor coordinates; (11b) is a data processor 2 that selects an injection thruster from the position of the North Star determined in (11a) and creates a signal instructing execution of injection; 02 is the Volaris sensor, ([, (141°as, as is (4a),
(4b), (4a), This is the position of the North Star on the Volaris sensor coordinates when the satellite is located at (4a). Agent Masuo Oiwa Figure 2 6 Figure 3 Figure 4

Claims (1)

[Claims] A three-axis attitude control satellite in a geostationary orbit is equipped with a stellar sensor that observes Polaris in the -pitch axis direction, a thruster that generates thrust in the one-pitch axis direction and the +pitch axis direction, and processes the stellar sensor output. Both thruster injection ON/O
An orbit control device for an artificial satellite, characterized in that a signal instructing FF is created, and in accordance with the signal, a thruster is injected so as to bring the orbital inclination angle to zero, and the orbital inclination angle is always maintained near zero.