JPS58183393A - Control system of 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 This relates to an attitude control method for controlling the orbit by operating the gas jet device of this QE4tj bias momentum type three-axis stable satellite. A gas jet device that generates torque around the roll, pinch, and yaw axes by using a device that detects one attitude angle difference per roll, pitch, and yaw axes for attitude control during satellite orbit control. was activated to remove attitude angle errors around each of the three axes.

By the way, in the case of a three-axis stable satellite, roll differences and pitch errors can be detected using an optical attitude angle error detector such as an earth sensor, but in order to detect a 1-yaw difference, a gyro or star sensor etc. A complicated and expensive attitude angle one-difference detector is required. Therefore, in this invention, we propose a control method that can accurately control the attitude of an artificial satellite by using only a sensor similar to an earth sensor as an attitude angle error detector. The attitude control method during orbit control will be explained.

FIG. 1 shows an embodiment of the present invention. In the figure, (1) #"ii roll axis, ) is a pinch axis, +31 Fi
Yaw axis, +41Vi attitude angle error detector as earth sensor, (5) a momentum wheel whose axis of rotation is parallel to the pitch axis (2), (6) , f71ij) pair of lux-generating gas jet devices, (81 , (91 is a pair of gas jet devices that generate thrust in the roll axis direction.

(In the main body of the 11Vi satellite, αυ is the earth. Figure 2 is a diagram showing the installation of the torque generating gas jet device , 04 ke gas jet device + 61 , ()) offset angle. Figure 3 shows the roll axial thrust gas '
G of the component equipment used for attitude control when operating the jet device (81 straddle (9) to perform orbit control)
In the figure, q3 is the drive control circuit for the momentum wheel (5).

The torque vectors generated by the torque generating gas jet devices +61 and +71 are roll @ (1) and yaw @ (3).
It is offset by an angle αa from the positive direction of the roll axis (1) to the negative direction of the yaw axis f31, and does not coincide with the yaw axis (3).

The momentum wheel (5) rotates at a constant rotational speed, and due to the jarro rigidity generated by the angular momentum, the satellite main body OI is stabilized along three axes.

In such a configuration, the cassjet devices (8) and (9
) to the orbital side! When attaching #, (81, +91 installation may generate disturbance torque due to errors, etc.)

Due to this disturbance torque, the satellite main body OQ performs a nutation motion and changes the direction of the angular motion lid vector generated by the momentum wheel (5). In order to suppress these movements and changes, the roll error of the earth sensor (4) is input to the control circuit I, and the offset gas jet devices @ +61 and +71 are operated according to the error. Of the torque generated by the gas jet devices +61 and f7+, the torque component in the roll axis direction has the effect of suppressing nutation motion, and the torque component in the yaw axis direction suppresses the angular motion t vector of the momentum wheel (5). The Ω gas jet device f81 has the effect of suppressing fluctuations. (The roll error and 1 yaw difference that remain when the operation of the Ω gas jet device f81 is stopped and orbit control is completed are removed by using roll-yaw conversion due to the orbital motion of the satellite. .What is roll/yaw conversion?

This is a phenomenon in which the yaw-axis direction component of the generated angular momentum vector of the momentum wheel appears as a roll-axis direction component after one quarter of the orbit of the satellite. Since the roll error can be detected by the earth sensor, it can be removed by operating the offset gas jet devices 1 +61 and +71. Therefore, roll and yaw errors can be completely eliminated in one quarter of the orbit of the satellite.

In addition, the pinch error can be removed during and after the orbit control, since the pinch error can be detected by the earth sensor, and the operation of the incidental cass jet device that generates a torque of one pinch axis and the IP1 rotation of the momentum wheel are necessary. The torque can be generated by adjusting the torque.

[152] As explained above, according to the present invention, an attitude angle error detector (e.g., an earth sensor) for detecting roll error and pinch error and an offset gas jet device
By using tf, the bias momentum method = @V
There is an advantage that attitude control during orbit control of a W artificial satellite can be performed without using a device for detecting a 1-yaw difference.

[Brief explanation of the drawing]

Figure 1 is a diagram showing the configuration of a three-axis stable artificial satellite implementing this invention, Figure 2 is a diagram showing the storage arrangement of the Kasjet device shown in Figure 1, and WIs diagram. Vi+I! 4
This is a diagram showing the flow of (g) between components.
31...Yaw axis, a4)...Attitude angle error detector, (
5) Momentum wheel, (6) Torque generating gas jet device, (71-9° torque generating gas jet device, t8) Roll m direction thrust generating gas jet device, (9) ...Roll axial thrust generating gas jet device, ■0...Satellite main body, 0υ...Earth, O
3... Torque generating gas jet device drive control circuit, 0
3... Momentum wheel drive control circuit, O4...
・Offset angle α. In the drawings, the same or corresponding parts are designated by the same reference numerals. Agent Jo Kuzuno - Figure 1 Figure 3 ゛//' Figure 2

Claims (1)

[Claims] An attitude angle error detector that detects attitude angle errors due to roll and pinch axes, a momentum wheel that rotates at a nearly constant rotation speed with the pinch axis as the rotation axis, and a gas jet device that generates thrust for orbit control. , in the attitude control system of a three-axis stable satellite equipped with a gas jet device that generates torque in a direction other than the roll axis and yaw axis within the plane formed by the roll axis and yaw axis, the thrust generating gas jet device is operated. When controlling the orbit by controlling the orbit, the attitude angle error detector and the torque generating gas jet device are used to control the satellite to a stable attitude in three axes, and the operation of the thrust generating gas jet device to control the orbit. After the satellite has stopped, the attitude errors around the roll axis, pitch axis, and yaw axis of the satellite can be removed using the attitude angle error detector and the torque generating gas jet device. attitude control method.