JPS58126298A - Control system of 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 The present invention relates to an orbit control method for an artificial satellite that prevents nutrition that occurs during the orbit control of a typical spin satellite from remaining after the orbit control.

The orbit control method for a single satellite that controls the orbital inclination of a conventional spin satellite is attached to the outside of a satellite that is rotating around one axis (hereinafter referred to as spin), and the thrust direction is set in the direction of the spin axis. The set thrust generator (hereinafter referred to as the thruster) is activated and injects the number of fixed time widths estimated by commands from the ground station, but the thruster thrust vector does not penetrate the center of gravity of the satellite. In this case, a torque perpendicular to the spin axis is generated, causing nutation of the spin axis. As a result, the attitude of the first artificial satellite fluctuates for a while after control, and the pointing accuracy of the antenna onboard the satellite, which points toward the earth, decreases.
The drawback was that there was a long period of time during which communication between satellites on the ground would be lost.

The present invention provides an orbit control method for an artificial satellite that aims to reduce the residual double knee John after injection by setting the thruster injection time during orbit control to 90% in order to eliminate the above-mentioned conventional drawbacks. It is something to do.

FIG. 1 is a schematic diagram of a satellite for explaining the present invention. In Figure 1, (1) is the spin satellite i2+Fi spin axis, (3) is the thruster, (4) the company speedometer, (5) is the sensitivity axis vector, (6) is the thruster injection direction, and (7) is the thruster. and the mounting phase angle of the accelerometer. As shown in Figure 1, the sensitivity axis vector (5) is the spin axis of the satellite (2).
nutrition detection sensor (
(hereinafter referred to as an accelerometer) (4) When a spin satellite (11) generates nutation motion by thruster injection during orbit control, it has an amplitude proportional to the magnitude of the nutation, and has the same frequency as the nutation motion. This new chiron has a sine wave output of
The horizontal axis angular velocity vector in the Xs ys plane, which is generated by the angular velocity of the
) is expressed as the perceived magnitude.

Fig. 2 shows the accelerometer output (9) and the accelerometer output (9) when the thruster injection stop time is set and orbit control is carried out so that no new chisicon remains, and the orbit control is performed in the satellite shown in Fig. 1 according to the present invention. The rotation angle t1· and the thruster pulse (8) are shown, respectively. Since the nutrition angle repeats increases and decreases in the rotation period I, if the thruster injection is terminated when it reaches zero, the nutrition after orbit control can be reduced. This injection end time can be indicated as the elapsed time I from the zero cross point (I3) of the accelerometer output (9). Using pulse 03' (i = fully generated, after the specified elapsed time of 0 from that pulse, the thruster injection end signal (to)
It is enough to generate one. Here, the nutrition period and the value of β(7) in FIG. 1 are known.

This elapsed time α instruction is stored in the satellite by a command from the ground station, and the overflow loss signal pulse α
If you start timing after the crash occurs, you can go to the dog.

As described above, by using the accelerometer force signal, this invention can set the thruster injection time to make the nutrition less sensitive after orbit control, and improve the accuracy of the satellite's on-board earth pointing antenna after injection. , it is possible to prevent communication between the ground and the satellite from disappearing.

[Brief explanation of the drawing]

FIG. 1 is an explanatory diagram of a spin satellite equipped with an accelerometer and thruster necessary for the present invention, and FIG. 2 is a signal output diagram when orbit control is performed using the method according to the present invention. In the figure, (1) is a spin satellite, (2) is a spin axis, and (3)
is the thruster, (4) is the accelerometer, (5) is the sensitivity axis vector, +6) is the thruster injection direction, (7) is the installation phase angle of the thruster and accelerometer, (8) is the thruster angle, (9)
) is the acceleration output, (II is the nutrition angle, αυ
is the nutrition period, a is the zero cross point, U is the zero cross detection pulse, 04 is the time until the end of the thruster injection, and S is the end pulse of the thruster injection. Agent Shin Kuzuno −

Claims (1)

[Claims] A control thrust generator attached to the outer end of the satellite in the rotational radius direction with the thrust axis parallel to the spin axis, and a nutrition detection sensor that detects the satellite's nutrition movement as rotational movement around an axis perpendicular to the spin axis. and
In an orbit control method that controls the inclination of the orbit in which a spin satellite is flying, after operating the control thrust generator, the control thrust generator stop timing is determined by a sine wave obtained from the two-knee joint detection sensor. 1. An orbit control method for an artificial satellite, characterized in that a command is given from a ground station as the elapsed time from a predetermined reference point of a signal, so that no two-task deviation remains after orbit control of a spin satellite.