JPH03246198A - Attitude control device for space navigation body - Google Patents

Abstract

PURPOSE:To prevent the contamination in the space by controlling the first and second brake sections for controlling the brake of the first and second rotors and providing a means to control the attitude of a space navigation body and a heat controlling device to radiate the heat generated by the operation of the first and second braking sections. CONSTITUTION:An attitude control device of a space navigation body is coaxially provided with the first and second rotors 12a and 12b, wherein generated heat is controlled by a radiator 19, through the first and second brake sections 18a and 18b, and restricts a momentum to zero and executes constant attitude control by inversely synchronizing these rotors 12a and 12b with each other. In addition, by braking either the rotor 12a or 12b through the braking section 18a and 18b, a momentum is variably set, and torque corresponding to the variation is generated to change the attitude. In this case, since a thruster requiring propellant as fuel is not used, life is prolonged, and the prevention of contamination in the space can be realized.

Description

DETAILED DESCRIPTION OF THE INVENTION [Object of the Invention] (Industrial Application Life) The present invention relates to an attitude control device used to control attitude changes of a space vehicle such as an artificial satellite.

(Prior Art) Generally, this type of attitude control device performs steady attitude control using an attitude control drive wheel, and also performs high-speed attitude changes using a thruster. That is, as shown in FIG. 3, in the drive wheel, a rotor 1 is rotatably provided in the spacecraft via a bearing 2, and the rotor 1 is rotationally driven via a drive unit 3 of a motor. The attitude of the spacecraft is controlled by using changes in torque and momentum that occur around the rotation axis. The output torque of this drive wheel is a value that depends on the shape and dimensions of the rotor 1, the friction of the bearing 2, and the output of the drive unit 3. Also, by minimizing the frictional force, highly accurate and stable attitude control can be achieved. Realize. That is, since the output torque for control is obtained by the electromagnetic force of the drive section, a large output cannot be expected.

Therefore, when performing a high-speed attitude change, it is difficult to use the drive wheel, so the thrusters are driven and controlled to perform a rapid attitude change.

However, in order to perform high-speed attitude changes, the attitude control device described above is equipped with a thruster that uses propellant as fuel, and since there is a limit to the amount of propellant that can be used in the thruster, its lifespan is short. At the same time, there was the problem of contaminating outer space.

In addition, this type of attitude control device uses a gyroscopic effect to generate a desired torque to perform attitude control and attitude change.
MG) has also appeared.

However, since this attitude control device using a CMG must be provided with a complicated mechanism including a gimbal mechanism, there are problems in that it is large and heavy, and requires a large amount of power when required.

(Problem to be solved by the invention) As stated above, conventional attitude control devices have short lifespans, pollute space, are large and heavy, and consume large amounts of power. I had a problem.

This invention was made in view of the above-mentioned circumstances, and is a space system that has a simple configuration, can realize highly accurate attitude change control over a long period of time, and can prevent contamination of outer space. The purpose of the present invention is to provide an attitude control device for a navigation vehicle.

[Structure of the Invention] (Means for Solving the Problems) The present invention provides first and second rotors that are coaxially provided in a spacecraft and are driven to rotate in opposite directions, and the first and second rotors. first and second braking units that brake the first and second rotors; and controlling the first and second braking units to brake the first and second rotors to control the attitude of the spacecraft. The attitude control device for the spacecraft includes a control means for controlling the spacecraft, and a heat control means for dissipating heat generated by the operation of the first and second braking sections.

(Function) According to the above configuration, when the first and second rotors are rotationally driven in synchronization, the momentum is canceled and set to zero, and steady attitude control is executed, and one of the rotors is rotated synchronously. When the vehicle is braked via the first and second brake sections, the momentum is changed, a large torque corresponding to the change is generated, and an attitude change such as a trajectory change is executed. The first and second rotors and the first and second braking parts are thermally controlled to a constant temperature by dissipating heat generated during braking by the heat control means.

(Example) Hereinafter, an example of the present invention will be described in detail with reference to the drawings.

FIG. 1 shows an attitude control system for a spacecraft according to an embodiment of the present invention, and IQ in the figure is a housing filled with oil 11. In FIG. The housing 10 includes first and second rotors 12a.

12b is rotatably housed coaxially via a bearing 13. The first and second rotors 12a, 12b are connected to rotor drive sections 14a, 14b, respectively, and these rotor drive sections 14a, 14b are connected to a synchronous circuit 15. This synchronization circuit 15 is connected to a control section 16.

Further, the housing 10 includes first and second braking parts 17a.
, 17b are the first and second rotors 12a.

12b. These first and second brake parts 17a, 17b are connected to brake drive parts 18a, 18b, and these brake drive parts 18a, 18b are connected to the control part 16. The control section 16 operates the synchronous circuit 15 and the brake drive sections 18a and 1 in response to the command signal.
8b to perform steady attitude control and attitude change control.

Furthermore, the housing 10 has a heat radiator 19 at one end thereof.
are set up consecutively. The radiator 18 is connected to the first and second braking parts 17
The heat generated by the operation of rotors a and 17b is thermally conducted to cool the heated oil, and the heated oil is transferred to the first and second rotors 12a and 12.
b. Execute thermal control of the first and second braking units 17a and 17b.

Note that the first and second braking parts 17a and 17b are as follows:
Various mechanisms such as a rotor clamping method and a disc pressure contact method are applicable.

In the above configuration, the control unit 16 drives and controls the rotor drive units 14a and 14b via the synchronization circuit 15 in response to the command signal, and synchronizes the first and second rotors 12a and 12b in mutually opposite directions. Drive rotation. Then, the first and second rotors 12a.

12b, as shown in FIG. 2, as it rotates, each momentum cancels out and reaches a predetermined rotational speed at time T1 while maintaining zero momentum. When the attitude change control signal is input as a command signal, the control unit 16 controls the brake drive unit 18 corresponding to this attitude change signal.
One of the brake drive units 18a and 18b is operated for a time T.
2, the rotor drive section 14a is stopped.

Then, the first rotor 12a is stopped at time T3, and only the second rotor 12b is driven to rotate during the time period 12 to 13, and as the rotor 12b rotates, IR is the rotor inertia, and ωR is the rotor due to braking. If it is the amount of change in angular velocity, then the large torque corresponding to the momentum (1-IR・ω
R) occurs and the attitude change of the spacecraft is executed.

Then, at time T4, the control unit 16 operates, for example, the other brake drive unit 18b, and also operates the rotor drive unit 1.
4b to brake the second rotor 12b, and the first and second rotors 12a.

The attitude change is completed in a state in which both drives of 12b are stopped. After that, the control unit 16 controls the brake drive unit 1
8a and 18b, and the rotor drive unit 14
a, 14b to drive and control the first and second rotors 12.
a and 12b are rotated in synchronization with each other in opposite directions to perform steady attitude control.

Note that in a series of attitude control states including the above attitude change, the first and second rotors 12a.

The amount of heat accompanying the rotation and braking of the housing 12b is transferred to the oil 11 in the housing 10, and the heat is radiated by one radiator through the oil 11, thereby controlling the heat.

In this way, the spacecraft attitude control device controls the first and second rotors 12a and 12b, which are thermally controlled by radiating heat from the radiator 19, by the first and second braking parts 18a,
18b, and by driving the first and second rotors 12a and 12b to rotate in synchronization with each other in opposite directions, the momentum is controlled to zero momentum and steady attitude control is performed. At the same time, by braking one of the first and second rotors 12a and 12b via the first and second braking parts 18a and 18b, the momentum is variably set and a torque corresponding to the change is generated. , configured to perform attitude changes. According to this, by being able to achieve high-speed attitude changes such as orbit changes without using conventional propellant-fueled thrusters, it is possible to extend the life of the spacecraft and prevent pollution of outer space. . Moreover, compared to the conventional CMG, the structure can be simplified, thereby promoting reduction in size and weight.

Note that in the above embodiment, a case has been described in which the configuration is configured to perform both steady attitude control and high-speed attitude change control, but the present invention is not limited to this. For example, only high-speed attitude change control is performed, and steady attitude change control is performed. It is also possible to arrange for the control to take place using conventional drive wheels.

Further, in the above embodiment, the first and second rotors 12a and 12b are braked when the attitude change is completed, but the invention is not limited to this.
For example, it is also possible to perform steady attitude control by driving the braked one again.

Therefore, it goes without saying that the present invention is not limited to the above embodiments, and that various modifications can be made without departing from the spirit of the invention.

[Effects of the Invention] As detailed above, according to the present invention, highly accurate posture change control can be realized over a long period of time with a simple configuration.
Furthermore, it is possible to provide an attitude control device for a spacecraft that can prevent contamination of outer space.

[Brief explanation of drawings]

Fig. 1 is a configuration diagram showing an attitude control device for a spacecraft according to an embodiment of the present invention, Fig. 2 is a characteristic diagram shown to explain the operation of Fig. 1, and Fig. 3 is a conventional attitude control device. FIG. 3 is a diagram shown to explain a control device. 10...Housing, 11...Oil, 12a. 12b...first and second rotors, 13...bearings,
14a, 14b... Rotor drive unit, 15... Synchronous circuit, 16... Control unit, 17a, 17b... First and second braking unit, 18a, 18b... Brake drive unit, 1
One... radiator.

Claims (1)

[Claims] First and second rotors that are coaxially provided on the spacecraft and are driven to rotate in opposite directions, and first and second rotors that brake the first and second rotors. a braking unit; and controlling the first and second braking units to control the first and second braking units.
A space vehicle characterized by comprising: a control means for controlling the braking of the rotor of the spacecraft to control the attitude of the spacecraft; and a heat control means for dissipating heat generated by the operation of the first and second braking parts. Attitude control device for navigation vehicles.