JPH0787007B2 - Disk type recording device for space - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a disk type recording device mounted on a spacecraft for recording and reading various data on the spacecraft, and in particular, does not adversely affect the attitude control of the spacecraft. The present invention relates to a disk-type recording device for space, which has a disk rotating part.

[0002]

2. Description of the Related Art Generally, as a recording device for recording and reading various data, there is a general commercial disk type recording device used on the ground. A disc-type recording device for recording and reading data has not been developed yet.

A general commercial disk type recording apparatus, for example, a magneto-optical disk recording apparatus, rotates a disk-shaped magneto-optical disk 101, which is a recording medium, at a high speed by a spindle motor 102, as shown in the schematic diagram of FIG. A head 103 and an exciting coil 104, which are installed close to the magneto-optical disk 101, are configured to write / read information and data. In the figure, 105 is a motor control device, 106 is a head servo control device, 107 is a laser drive / signal processing circuit, and 108 is an excitation coil control circuit. Such a basic configuration has a magnetic disk, an optical disk, or a disk-type recording. If it is a device, it is basically the same.

[0004]

By the way, when a general-purpose disk type recording apparatus having such a structure is mounted on a spacecraft and used, the angular momentum and torque generated by the high-speed rotating disk cause the attitude control of the spacecraft. And adversely affect orbit control. That is, specifically, disturbance of the attitude of the spacecraft,
Or, due to the so-called gyro rigidity of an object having angular momentum, a large amount of unnecessary fuel consumption of a gas jet for attitude control of a spacecraft mounted on a spacecraft may be caused,
Further, it has an unfavorable influence on the spacecraft system such as an excessive load on the flywheel for attitude control.

The present invention has been made to solve the above-mentioned problems that occur when a conventional disk type recording device is mounted on a spacecraft. The disk rotation is performed so as not to adversely affect the attitude control of the spacecraft. It is an object of the present invention to provide a disk-type recording device for space, which constitutes a unit.

[0006]

SUMMARY OF THE INVENTION In order to solve the above problems, the present invention provides a disk type recording apparatus mounted on a spacecraft, wherein a disk rotating unit is configured to drive an even number of disks. In addition, the disk rotating portion is equally divided into two parts, and each divided disk rotating portion is configured to rotate in synchronization with each other in opposite directions.

As described above, the multi-disk rotating part is equally divided into two parts, and each divided disk rotating part is configured to rotate in synchronization with each other in opposite directions. The generated angular momentum and torque cancel each other out, and this can prevent adverse effects on the attitude control of the spacecraft.

[0008]

EXAMPLES Next, examples will be described. FIG. 1 is a schematic view showing an embodiment of a space disk type recording apparatus according to the present invention. In this embodiment, the present invention is applied to a magneto-optical disk recording apparatus, and in order to increase the data transfer rate at the time of recording and reproducing, parallel multiplexing of recording / reproducing data by a multi-head (multi-channel) structure is carried out. Conversion to
Further, in order to increase the capacity, the multi-disc rotating part is configured to be able to rotate and drive eight discs. In the figure, 1A and 1B respectively divide a multi-disk rotating portion into two parts so as to be arranged so as to face each other, and four magneto-optical disks 2A-1 and 2A-, respectively.
2, 2A-3, 2A-4; 2B-1, 2B-2, 2B-
3 and 2B-4 is a divided disk rotating unit configured to rotate. Each of the divided disk rotating parts 1A and 1B is
Spindle motors 3A and 3B are provided respectively, and the magneto-optical disks are rotationally driven by the motors 3A and 3B via rotating shafts 4A and 4B. At that time, the spindle motors 3A, 3B are connected to the disk servos 5A, 5B.
Thus, they are rotated in the opposite directions in synchronization with each other.

Each magneto-optical disk 2A-1, ... 2A
-4, 2B-1, ..., 2B-4 are provided with a head 6 for irradiating a laser beam and an exciting coil 7 for giving an external magnetic field in close proximity to each other, and the divided disk rotating portions 1A, 1B.
Magneto-optical disks 2A-2, 2A-3, 2B arranged in the middle other than the magneto-optical disks arranged above and below
In −2 and 2B-3, since both sides are used, heads and exciting coils for the front surface and the back surface are arranged. In the figure, reference numeral 8 denotes a front surface internal controller for controlling the front surface head and the exciting coil, and reference numeral 9 denotes a rear surface internal controller for controlling the rear surface head and the exciting coil.

In the disk type recording apparatus having the above-mentioned structure, the spindle motors 3A and 3B controlled by the disk servos 5A and 5B synchronize the divided disk rotating portions 1A and 1B at high speed and in reverse. The recording / reading operation is performed by rotating the head 6 and the exciting coil 7. In this case, the respective discs of the divided disc rotating portions 1A and 1B arranged to face each other are synchronously reversely rotated, so that the angular momentum and the torque generated in the respective discs are offset.

In the above-mentioned embodiment, the two divided disk rotating parts are arranged so as to face each other for reasons such as compact mounting, but in order to cancel the angular momentum, the generated angular momentum is to be offset. It suffices that the vectors are antiparallel to each other, and if such a configuration is adopted, the two split disk rotating parts may be arranged in any manner.

For example, two divided disk rotating parts may be arranged side by side so that the generated angular momentum vectors are antiparallel to each other, and the two divided disk rotating parts may be separated from each other in the satellite. Dispersed and arranged on the inner plane,
The generated angular momentum vectors may be antiparallel to each other.

As for the method of synchronous reverse rotation, in the above-mentioned embodiment, two separate disk rotating parts are provided with separate spindle motors so that the synchronous reverse rotation is electrically controlled. It is also possible to share one spindle motor and to perform synchronous reverse rotation by a mechanical power transmission mechanism such as a gear.

Although the redundant head is omitted in the embodiment shown in FIG. 1, a front head 6A and a back head 6B are provided on the front and back surfaces of the magneto-optical disk 2 as shown in FIG. In addition to the provision, the front surface redundant head 6A 'and the back surface redundant head 6B' may be provided to form a redundant structure which is important for high reliability as a space-mounted device.

Further, the two divided disk rotating parts can be made redundant with each other. In that case, even if one of them fails, the minimum function of the recording device can be maintained.

[0016]

As described above on the basis of the embodiments,
According to the present invention, since the multi-disk rotating part is divided into two parts and the divided disk rotating parts are rotated synchronously in mutually opposite directions, the generated angular momentum and torque are offset. However, it is possible to prevent adverse effects on the attitude control of the spacecraft.

[Brief description of drawings]

FIG. 1 is a schematic configuration diagram showing an embodiment of a space disk type recording apparatus according to the present invention.

FIG. 2 is an explanatory diagram showing a rotation mode of a divided disk rotation unit.

FIG. 3 is a diagram showing a configuration example in which a head has a redundant configuration.

FIG. 4 is a schematic diagram showing a configuration example of a disc type recording device for general commercial use.

[Explanation of symbols]

1A, 1B Split disk rotating part 2A-1, ... 2A-4, 2B-1, ... 2B-4 Magneto-optical disk 3A, 3B Spindle motor 4A, 4B Rotation shaft 5A, 5B Disk servo 6 Head 7 Excitation coil

Claims (2)

[Claims] 1. A disk type recording device mounted on a spacecraft, wherein the disk rotating part is configured to drive an even number of disks, and the disk rotating part comprises two disks.
A disk-type recording device for space, characterized in that it is divided equally into two parts, and the divided disk rotating parts are rotated in synchronization in mutually opposite directions to cancel the generated angular momentum and torque. 2. The space disk type recording apparatus according to claim 1, wherein the divided disk rotating parts have a redundant configuration.