JPS5836799A - Reaction wheel for controlling 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 a rear axle wheel for attitude control of an artificial satellite.

For example, three-wheeled attitude control satellites often use a retekshi wheel as an actuator for attitude control. That is, the rotational moment of the satellite body changes due to the disturbance torque acting on the satellite body, resulting in a satellite attitude error. The center error is detected by a sensor or the like, and based on this detection signal, the attitude control logic generates a wheel drive signal tube (by the rear section), and the rotation speed of the rear axis wheel is controlled to increase or decrease using this drive signal. At this time, the satellite attitude error is corrected by the reaction torque generated in the reaction wheel.

In other words, the rotational moment of the satellite main body caused by the disturbance torque is absorbed by the rotational moment (K) of the Linux engine wheel, and the rotation of the satellite main body is brought to zero to maintain the attitude of the satellite.

Part 1II shows the basic structure of a conventional rear axle wheel. That is, the rotor 1 is attached to the shaft 1 through the bearing 1, and the rotor 1 is attached to the shaft 10 through the bearing 1.
4 is a stator which is excited by the wheel drive signal and drives the rotor 1t. These stators4. Four-ta 1. One shaft is stored in case 5FE3 and connected to one controller.
By the way, the polarity of disturbance torque, etc. that acts on the satellite is not always constant. As a result, the rotational direction of the rotor of the wheel may be reversed. At the moment when the rotor reverses, the rotor temporarily stops with respect to the shaft 7HC, and at this time, a stationary band is created due to the influence of the solid friction ring of the bearing interposed between the rotor and the shaft. Therefore, unless the excitation signal to the stator reaches a certain value or higher, the rotor will not start reversing from a stopped state.Therefore, when the rotation direction of the rotor is reversed, the attitude error of the satellite will increase. Ta.

However, due to the solid friction of the bearing between the shaft and rotor, the satellite attitude error becomes large during low I reversal (called wheel zero cross).

The present invention has been made to eliminate the above-mentioned drawbacks, and by coaxially providing a plurality of rotors with a common rotational axis vector direction, it is possible to prevent wheel zero crossings and improve the accuracy of satellite attitude control. The present invention provides an axis wheel for controlling the attitude of an artificial satellite.

An embodiment of the present invention will be described in detail below with reference to the drawings.

In Fig. 2, 21 is, for example, a shirt integrally protruding from the case 22)% J x is this shirt) JJK
1C) A first rotor 25 rotatably provided via a bearing 24 is a first stator disposed near the TGLOA-mechanical 21. 1# is the second bearing provided on the outer periphery I[K of the first rotor 2J, 2
1 is connected to the first rotor 1 via this second bearing 2C.
A second quadrupler, 21, rotatably provided on the circumference jP of 1;
is a second stator disposed near the second rotor 2r.

These rotors xs, xv, stators 25.degree., 28, etc. are housed in a case 21 and constitute one reactor wheel, on which, for example, a three-axis central control wheel is mounted.

In the above-mentioned rear engine wheel, when an excitation signal is supplied to each stator 25, 211 from the V-shaped portion (not shown) of the damping control valve, the first rotor 23 is moved from the fixed shaft. The second rotor 27 rotates for 210 revolutions.
The first rotor xst is considered to be a shaft and can rotate around the circumference of the first rotor IS. That is, the operation of the first bearing 24 is determined by the state of rotation of the first rotor 2S, and the operation of the second bearing 26 is determined by the state of relative rotation between the first rotor 23 and the second rotor 2r. be done.

Therefore, by appropriately specifying the rotational state of each rotor 23, 21, it is possible to prevent the occurrence of a zero cross of each I-23, 21, and a situation where each bearing x4, 26 stops momentarily does not occur. That is, the shaft 21.
Rotation difference between the first rotors 2S and the first rotor 2
3. Each rotor 13. By driving the IF, zero crosses can be prevented from occurring, satellite attitude errors caused by zero crosses can be prevented, and the accuracy of satellite attitude control can be improved.

In other words, according to the above-mentioned rear axle wheel, since the two rotors with the same rotational axis vector direction are coaxially provided, each rotation of the two rotors can be controlled separately, and the rotation of the two rotors can be controlled separately. Even if the polarity of the applied disturbance torque or the like is reversed by 1, the relative rotation between each rotor and the rotating shaft can be maintained, and zero crossings can be prevented from occurring.

Note that in the above embodiment, two rotors were provided coaxially, but three rotors were provided coaxially.
It is also possible to provide more than one rotor coaxially.

As described above, in the present invention, since a plurality of rotors having a common rotational axis vector direction are coaxially provided, the occurrence of wheel zero crossing can be prevented by rotating each rotor independently, thereby controlling the satellite attitude. It is possible to provide a rear axle transmission wheel for artificial satellite attitude control that can improve the accuracy of satellite attitude control.

[Brief explanation of the drawing]

Figure 1 (a), 弽) shows the conventional satellite attitude control reactor.
Partially cutaway perspective view and vertical cross-sectional view schematically showing the wheel, Figure 2! , 1) and (b) are a partially cutaway perspective view and a vertical cross-sectional view schematically showing an embodiment of a rear-axle flywheel for satellite attitude control according to the present invention. 21... Shaft, 23... First row 1.24-
@1 (2) Bearing, 25...1st X-chie 1.2
6... Second bearing, 27... Second roller,
28-Second stator.

Claims (1)

[Claims] A first rotor rotatably provided on the shaft via a first bearing, and a first rotor that drives the first rotor.
and a stator provided coaxially on the outside of the first rotor? At least one second rotor rotatably provided around the inner roller via a bearing between the rotor 3 and the second rotor, and a second stator that drives the second rotor. A rear axis wheel for artificial satellite attitude control that is characterized by