JP2000018950A - Gyrocompass - Google Patents

Abstract

PROBLEM TO BE SOLVED: To obtain a gyrocompass which can securely transmit abnormalities in respective parts of a device to the outside. SOLUTION: This gyrocompass has an inertial sensor unit 10 which detects the earth's axis, a system navigation unit 12 which performs output control, etc., over abnormality warning, a main CPU 13 which outputs a battery system abnormality signal Ia or device system abnormality signal Ib when the inertia sensor unit 10 or a battery unit 11 becomes abnormal and outputs byte data Ds representing abnormality when a parallel I/O.15 becomes abnormal, a control display unit 21 which has an operation function, etc., for setting and varying various operation parameters of the main CPU 13, alarm relays 18a1, 18a2, 18b1, and 18b2 which are driven with the battery system abnormality signal Ia, device system abnormality signal Ib, etc., and an alarm distribution board 6, which displays the abnormality of respective parts of the device.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gyrocompass used for measuring the azimuth of a general ship or a ship (hereinafter simply referred to as a ship).

[0002]

2. Description of the Related Art Conventionally, a gyro compass for measuring an azimuth angle with high accuracy has been installed in a ship. FIG.
FIG. 1 is a block diagram showing a schematic configuration of a conventional gyrocompass. In FIG. 1, reference numeral 1 denotes a system navigation unit that controls each unit of the apparatus. The operation of the system navigation unit 1 will be described later in detail. Reference numeral 2 denotes a battery unit that supplies power to each unit of the device in place of the power supply when power (not shown) supplied to each unit of the device is cut off. The battery unit 2 has a self-diagnosis function, and outputs a battery voltage drop signal Sbv when the output voltage of the battery drops, and a battery fault signal Sbi when a fault occurs in the battery. Output to

[0003] 3 is an inertial sensor for detecting the earth's axis,
This is an inertial sensor unit having a CPU (Central Processing Unit) and the like, and outputs a detection result to the system navigation unit 1 as inertial data Dk. The system navigation unit 1 calculates the azimuth using the inertia data Dk and the calculation parameters set therein, and then outputs this as azimuth data H. Further, the inertial sensor unit 3 outputs to the system navigation unit 1 an operation signal Sku indicating that the inertia sensor unit 3 is operating. Further, the inertial sensor unit 3 has a self-diagnosis function. When an abnormality occurs in its own function, the inertial sensor unit 3 outputs an inertial sensor unit abnormality signal Ski indicating the abnormality to the system navigation unit 1.

Reference numeral 4 denotes a control display unit, which has a display for displaying various calculation parameters used in the system navigation unit 1 and an operation unit used for setting / changing the various calculation parameters. The control display unit 4 has a self-diagnosis function in the same manner as the battery unit 2 described above. When an abnormality occurs in its function, the control display unit 4 outputs a control display unit abnormality signal Sci indicating the abnormality to the system navigation unit 1.
Output to

[0005] The system navigation unit 1
Indicates that an abnormality has occurred in the gyrocompass when any of the above-described battery voltage drop signal Sbv, battery abnormality signal Sbi, inertia sensor unit abnormality signal Ski, or control display unit abnormality signal Sci is input. An abnormal signal I is output.

Reference numeral 5 denotes a display, which displays an azimuth obtained from the input azimuth data H. Reference numeral 6 denotes an alarm switchboard, which has a plurality of alarm lamps provided corresponding to the inertial sensor unit 3, the battery unit 2, and the control display unit 4, respectively. When the abnormal signal I is input, the alarm switchboard 6 turns on an alarm lamp corresponding to the device indicated by the abnormal signal I.

[0007]

In the conventional gyro compass, when an abnormality occurs in each section of the apparatus, the parallel I / O of the system navigation unit 1 is not used.
An abnormal signal I is output to the alarm switchboard 6 via O (Input / Output). Therefore, in the conventional gyro compass, when the parallel I / O fails, no abnormality alarm is displayed on the alarm switchboard 6 even though an abnormality has occurred inside the gyro compass,
There was a serious drawback in that the identification and recovery of the abnormal location was greatly delayed. In particular, since the gyrocompass is the most important device among various instruments of a ship, the delay in the recovery of the abnormal location has a serious effect on the voyage of the ship. The present invention has been made under such a background, and an object of the present invention is to provide a gyrocompass that can reliably transmit an abnormality of each part of the device to the outside.

[0008]

According to a first aspect of the present invention, there is provided an inertial sensor for detecting an earth axis of the earth, control means for obtaining an azimuth angle based on a detection result of the inertial sensor, and the control means. A gyro compass having operating means for performing various operations on the first means, the first means being provided in the control means, and monitoring the abnormality of the inertial sensor means and the operating means, the first means being provided in the operating means, It is characterized by comprising a second abnormality monitoring means for monitoring the abnormality of the first abnormality monitoring means, and a display means for displaying the monitoring results of the first and second abnormality monitoring means.

According to a second aspect of the present invention, in the gyro compass according to the first aspect, the inertial sensor means includes:
When an abnormality has occurred in itself, the inertia sensor outputs an inertia sensor abnormality signal, the operation means outputs an operation means abnormality signal when an abnormality has occurred in itself, and the first abnormality monitoring means has the inertial sensor abnormality signal or When the operation unit abnormality signal is input, the monitoring result is regarded as abnormal.

According to a third aspect of the present invention, in the gyro compass according to the first or second aspect, the first abnormality monitoring means outputs a monitoring means abnormality signal when an abnormality has occurred in itself. The monitoring means is characterized in that when the monitoring means abnormality signal is input, the monitoring result is abnormal.

[0011]

Embodiments of the present invention will be described below with reference to the drawings. FIG. 1 is a block diagram showing a configuration of a gyro compass according to an embodiment of the present invention.
In this figure, parts corresponding to the respective parts in FIG. 2 are denoted by the same reference numerals, and description thereof will be omitted. In FIG. 1, 10
Is an inertial sensor unit having a self-diagnosis function in the same manner as the inertial sensor unit 3 shown in FIG. 2. The inertial sensor unit outputs an operation signal Sku and inertia data Dk during normal operation. Unit error signal S
Output ki.

Numeral 11 denotes a battery unit having a self-diagnosis function in the same manner as the battery unit 2 shown in FIG. 2. The battery unit 11 outputs a battery voltage drop signal Sbv when the battery voltage drops, and a battery voltage drop signal when an abnormality occurs in the battery. It outputs a battery abnormality signal Sbi.

Reference numeral 12 denotes a system navigation unit having the same function as that of the system navigation unit 1 shown in FIG. 2, and obtains an azimuth angle using the inertia data Dk and calculation parameters set therein.
In addition, output control of an abnormal alarm is performed. Details of the operation of the system navigation unit 12 will be described later. In the system navigation unit 12, 1
Reference numeral 3 denotes a main CPU that controls each unit of the system navigation unit 12. The operation of the main CPU 13 will be described later in detail.

Reference numeral 14 denotes a serial I / O to which a serial signal is input.
Is converted to a signal of a level that can be handled by. Reference numeral 15 denotes a parallel I / O to which a parallel signal is input, and converts the input signal into a signal of a level that can be handled by the main CPU 13. From the parallel I / O 15, the main CPU 1
Under the control of 3, the battery system abnormality signal Ia and the device system abnormality signal Ib are output.

Here, the battery system abnormality signal Ia
Is a signal generally representing the battery abnormality signal Sbi and the battery voltage drop signal Sbv output from the battery unit 11 described above, while the device system abnormality signal Ib
Is a signal generally representing the inertial sensor unit abnormal signal Ski output from the inertial sensor unit 10 described above and the control display unit abnormal signal Sci output from the control display unit 21 described later.

Reference numeral 16 denotes an interface circuit for interfacing between the main CPU 13 and the display 5, and outputs the azimuth data H generated by the main CPU 13 to the display 5. The above-described main CPU 13, serial I / O • 14, parallel I / O • 15, and interface circuit 16 are connected via a bus B1.

Reference numeral 17 denotes an inverter, which converts DC power supplied from the battery unit 11 into AC power. Reference numerals 18a1 and 18a2 are alarm relays driven by the battery system abnormality signal Ia, and output contact signals Ia1 and Ia2 to the alarm switchboard 6 when they are connected. 19 is
This is an OR circuit.
And a backup abnormality signal Ic to be described later are input. Reference numerals 18b1 and 18b2 are alarm relays driven by the output signal of the OR circuit 19, and output contact signals Ib1 and Ib2 to the alarm switchboard 6 when they are connected. 20 is
The output signal of the OR circuit 19 and the battery system abnormality signal Ia are input to each input gate.

Control display unit 21
Has functions similar to those of the control display unit 4 shown in FIG. 2, and has operation functions such as setting / change of various calculation parameters used in the main CPU 13 of the system navigation unit 12. Details of the operation of the control display unit 21 will be described later. In the control display unit 21, a CPU 22 controls each part of the control display unit 21, and the operation of the CPU 22 will be described later in detail.

Reference numeral 23 denotes a serial I / O for inputting and outputting a serial signal, and is provided to face the serial I / O 14 of the system navigation unit 12. Reference numeral 24 denotes a parallel I / O that inputs and outputs parallel signals.
/ O, which is provided facing the parallel I / O 15 of the system navigation unit 12. CPU 22, serial I / O 23 and parallel I
/O.24 are connected via a bus B2.

Reference numeral 251 denotes an abnormal state indicator, which is a CPU.
22 controls the system navigation unit 12
To indicate that an error has occurred. 252
Is an abnormal state indicator, which indicates that an abnormality has occurred in the inertial sensor unit 10 under the control of the CPU 22. 253 is an abnormal state indicator,
The control unit 22 displays that an abnormality has occurred in the battery unit 11.

Reference numeral 254 denotes an abnormal state indicator, which is a CPU.
22 control display unit 2
1 indicates that an abnormality has occurred inside. 25
5 indicates that the temperature inside the control display unit 21 has reached a certain temperature or higher under the control of the CPU 22. Reference numeral 26 denotes a light-emitting diode driven to be lit by an output signal of the OR circuit 20. When the light-emitting diode 26 is lit, it indicates that an abnormality has occurred inside the gyrocompass.

Next, the operation of the gyro compass according to the above-described embodiment will be described. First, when power is supplied to each unit of the apparatus, in the control display unit 21, the CPU 22 operates the operation signal Scu indicating that the control display unit 21 is operating.
Is output via the parallel I / O • 24. The operation signal Scu is transmitted to the system navigation unit 1
2 parallel I / O 15. Main C via bus B1
Input to PU13. Thereby, the main CPU 13
Recognizes that the control display unit 21 is operating normally.

The CPU 22 converts the above-mentioned operation parameters and the like as byte data Dc into a serial I / O
-Output via 23. Then, the byte data D
c is input to the main CPU 13 via the serial I / O 14 of the system navigation unit 12 and the bus B1. As a result, the main CPU 13 stores operation parameters and the like obtained from the byte data Dc in its own memory.

On the other hand, from the inertial sensor unit 10, the inertia data Dk, which is the detection result of the earth axis, and an operation signal Sku indicating that the inertial sensor unit 10 is operating are sent from the main CPU 1 of the system navigation unit 12.
3 is output. At this time, the inertial sensor unit abnormality signal Ski is not output from the inertial sensor unit 10. Thereby, the main CPU 13 recognizes that the inertial sensor unit 10 is operating normally.

Next, the main CPU 13 outputs the inertia data D
After obtaining an azimuth angle using k and the above-described calculation parameters, the azimuth angle is output as azimuth angle data H to the display 5 via the bus B1 and the interface circuit 16. Thus, the current azimuth obtained from the azimuth data H is displayed on the display 5.

If an abnormality occurs in the inertial sensor unit 10, an inertial sensor unit abnormality signal Ski is output from the inertial sensor unit 10 to the main CPU 13. Thereby, the main CPU 1
3 recognizes that an abnormality has occurred in the inertial sensor unit 10 and outputs an apparatus system abnormality signal Ib to the input gate of the OR circuit 19 via the bus B1 and the parallel I / O 15.

As a result, the output signal of the OR circuit 19 becomes "
H ", the alarm relays 18b1 and 18b2 come into contact, and the contact signals Ib1 and Ib2 are output from the alarm relays 18b1 and 18b2.
Is output to the alarm switchboard 6. As a result, the alarm switchboard 6
Displays an alarm indicating that the inertial sensor unit 10 has failed. When the output signal of the OR circuit 19 becomes “H”, the output signal of the OR circuit 20 becomes “H”, and the light emitting diode 26 is further turned on. That is, the lighting of the light emitting diode 26 notifies that an abnormality has occurred inside the gyro compass.

In parallel with the above-described alarm transfer operation, the main CPU 13 transmits byte data Ds indicating that an abnormality has occurred in the inertial sensor unit 10 to the bus B1,
Output via serial I / O. The byte data Ds includes various data used in the control display unit 21 in addition to the data indicating the abnormality, and is output even in a normal state.

The byte data Ds is transmitted to the serial I / O 2 of the control display unit 21.
3. Input to the CPU 22 via the bus B2. Thereby, the CPU 22 recognizes that an abnormality has occurred inside the inertial sensor unit 10 and
The control signal S is transmitted to the bus B2 and the parallel I / O.
4 for output. Thereby, the abnormal state indicator 25
2 indicates that an abnormality has occurred inside the inertial sensor unit 10.

Assuming now that the output voltage of the battery unit 11 has dropped, the battery unit 11 outputs a battery voltage drop signal Sbv to the main CPU 13. Thereby, after the main CPU 13 recognizes that an abnormality has occurred inside the battery unit 11,
The battery system abnormality signal Ia indicating the abnormality is output via the bus B1 and the parallel I / O 15.

Then, the battery system abnormality signal Ia
Are input to the alarm relays 18a1 and 18a2 and the input gate of the OR circuit 20, respectively. Thereby, the alarm relay 1
8a1 and 18a2 come into contact with each other and contact signals Ia1 and Ia1 are output from the alarm relays 18a1 and 18a2 to the alarm switchboard 6,
The alarm switchboard 6 displays that an abnormality has occurred inside the battery unit 11. When the battery system abnormality signal Ia is input to the input gate of the OR circuit 20, the output signal of the OR circuit 20 becomes “H”, and the light emitting diode 26 is further turned on.

Also, the system navigation unit 1
In parallel with the alarm transfer operation, the main CPU 13 transmits the byte data Ds indicating that an abnormality has occurred in the battery unit 11 to the bus B1 and the serial I / O • 1.
4 for output. As a result, the CPU 22 makes the bus B2, the parallel I / O • 2
4 to output the control signal S to the abnormal state indicator 253. As a result, the abnormal state indicator 253 indicates that an abnormality has occurred inside the battery unit 11. It should be noted that an abnormality has occurred in the battery of the battery unit 11, and the battery abnormality signal S
When bi is output, the same operation as the above-described operation when the battery voltage drop signal Sbv is output is performed.

Now, if an abnormality occurs inside the control display unit 21, the CPU
22 detects the abnormality and outputs a control display unit abnormality signal Sci indicating the abnormality via the bus B2 and the parallel I / O 24. The control display unit abnormality signal Sci is transmitted to the parallel I / O 1 of the system navigation unit 12.
5, input to the main CPU 13 via the bus B1.

Thus, after recognizing that an abnormality has occurred in the control display unit 21, the main CPU 13 outputs an apparatus system abnormality signal Ib via the bus B1 and the parallel I / O • 15. As a result, similarly to the above-described operation, the alarm switchboard 6 displays that an abnormality has occurred inside the control display unit 21, and the light-emitting diodes 26 of the control display unit 21 are turned on.

The CPU 22 of the control display unit 21 outputs a control signal S to the abnormal state indicator 254 via the bus B2 and the parallel I / O 24 in parallel with the alarm transfer operation. As a result, the abnormality status indicator 254 indicates that an abnormality has occurred inside the control display unit 21.

It is assumed that an abnormality has occurred in the parallel I / O 15 in the system navigation unit 12. In this abnormal state, even if an abnormality occurs in the inertial sensor unit 10, the battery unit 11, or the control display unit 21, the alarm relays 18a1 and 18a2 or the alarm relays 18b1 and 18b2
F Battery system abnormal signal Ia or device system abnormal signal Ib
Is not supplied.

However, the parallel I / O 15
Is detected by the main CPU 13 and the main C
The PU 13 outputs the byte data Ds indicating the abnormality via the bus B1 and the serial I / O • 14. The byte data Ds is input to the CPU 22 via the serial I / O 23 of the control display unit 21 and the bus B2.

Thus, the CPU 22 recognizes that an abnormality has occurred in the system navigation unit 12 and that the system navigation unit 12 cannot perform an alarm transfer operation. Next, the CPU 22
Is a backup abnormality signal Ic indicating that an abnormality has occurred inside the system navigation unit 12.
Is output via the bus B2 and the parallel I / O 24.

Thus, the backup abnormal signal I
c is input to the input gate of the OR circuit 19, and the output signal of the OR circuit 19 is set to “H”. Then, similarly to the above-described operation, the alarm switchboard 6 displays that an abnormality has occurred inside the system navigation unit 12, and the light emitting diode 26 emits light. Then, the operator recognizes that an abnormality has occurred inside the system navigation unit 12 based on the alarm display on the alarm switchboard 6, and starts recovery work.

Now, if an abnormality occurs in the main CPU 13 in the system navigation unit 12, the inertial sensor unit 10, the control display unit 21 or the battery unit is operated in the same manner as in the case of the parallel I / O 15. Even if an abnormality occurs in 11, the battery system abnormality signal Ia or the device system abnormality signal Ib is not supplied to the alarm relays 18a1 and 18a2 or the alarm relays 18b1 and 18b2.

However, when an abnormality occurs in the main CPU 13, the output of the byte data Ds stops, and the CPU 22 recognizes that an abnormality has occurred in the system navigation unit 12 by stopping the output.
Next, the CPU 22 transmits the backup abnormality signal Ic to the bus B2 and the parallel I / O · 2 in the same manner as the operation described above.
4 to the input gate of the OR circuit 19. Thus, an alarm indicating that the abnormality has occurred is displayed on the alarm switchboard 6, and the light emitting diode 26 emits light.

As described above, in the gyro compass according to the embodiment of the present invention, even if an abnormality occurs in the system navigation unit 12, the abnormality is detected by the control display unit 21 and the control is performed. The display unit 21 has a backup function of transferring an alarm to the alarm switchboard 6. Therefore, according to the gyro compass according to the embodiment, an effect is obtained that the abnormality of each part of the device can be reliably transmitted to the outside.

[0043]

According to the present invention, the first and second abnormality monitoring means have a redundant configuration. Therefore, even if an abnormality occurs in the first abnormality monitoring means and a correct monitoring result is not displayed on the display means. On the other hand, the correct monitoring result is displayed on the display means by one of the second abnormality monitoring means, so that an effect that the abnormality of each part of the apparatus can be reliably transmitted to the outside can be obtained.

[Brief description of the drawings]

FIG. 1 is a block diagram illustrating a configuration of a gyro compass according to an embodiment of the present invention.

FIG. 2 is a block diagram showing a schematic configuration of a conventional gyrocompass.

[Explanation of symbols]

6 alarm switchboard (display means) 10 inertia sensor unit (inertia sensor means) 12 system navigation unit (control means) 13 main CPU (first abnormality monitoring means) 15 parallel I / O (first abnormality monitoring means) 21 control Display unit (operation means) 22 CPU (second abnormality monitoring means) Ski Inertial sensor unit abnormality signal (inertial sensor abnormality signal) Sci Control display unit abnormality signal (operation means abnormality signal) Ds Byte data (monitoring means abnormality signal)

Claims (3)

[Claims] 1. A gyro compass comprising: inertial sensor means for detecting the earth axis of the earth; control means for obtaining an azimuth angle based on the detection result of the inertial sensor means; and operating means for performing various operations on the control means. A first abnormality monitoring means provided in the control means for monitoring an abnormality of the inertial sensor means and the operation means; and a second abnormality monitoring means provided in the operation means for monitoring an abnormality of the first abnormality monitoring means. A gyro compass comprising: an abnormality monitoring means; and a display means for displaying a monitoring result of the first and second abnormality monitoring means. 2. The inertial sensor means outputs an inertial sensor abnormality signal when an abnormality has occurred in the inertia sensor means, and the repeating means outputs an operation means abnormality signal when an abnormality has occurred in the inertia sensor means. 2. The gyro compass according to claim 1, wherein the abnormality monitoring means sets an abnormal monitoring result when the inertial sensor abnormality signal or the operation means abnormality signal is input. 3. The first abnormality monitoring unit outputs a monitoring unit abnormality signal when an abnormality occurs in itself, and the second monitoring unit outputs a monitoring result when the monitoring unit abnormality signal is input. 3. The gyro compass according to claim 1, wherein the gyro compass is abnormal.