JP2000025698A - Magnetic torquer control device for artificial satellite - Google Patents

Abstract

PROBLEM TO BE SOLVED: To make a current supplied to a magnetic torquer constant and also lessen a magnetic torquer control device and facilitate the loading property of an artificial satellite by outputting a control current detected by a control current detector to the magnetic torquer. SOLUTION: In the pulse width modulation circuits 12a-12c of a magnetic torquer control device 7, the pulse width of the control currents 8a-8c detected by control current detectors 16a-16c is moved by a control feedback signal 16. While, a primary electric source 4 is turned on and off by on/off circuits 11a-11c according to the indication of the control order signal 6 issued by a posture control device 5. The output of the on/off circuits 11a-11c is outputted to the magnetic torcas 9a-9c as the control currents 8a-8c controlled to a constant by the pulse width signals 13a-13c of the output of the pulse width modulation circuits 12a-12c in the switching circuits 14a-14c. Thereby, a stable control is carried out for the temperature change of the magnetic torcas 9a-9c and also a magnetic torquer control device 7 can be minified.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a magnetic torquer control device used for attitude control of a satellite.

[0002]

2. Description of the Related Art FIG. 3 schematically shows an example of a conventional attitude control device, a magnetic torquer, and a magnetic torquer control device used for attitude control of a general artificial satellite. Reference numeral 1 denotes a solar panel that generates power required by each device mounted on an artificial satellite by sunlight, 2 denotes a power generated by the solar panel 1, and 3 denotes a power 2 generated by the solar panel 1. A power supply device for supplying each device mounted as a primary power source with a stable voltage; 4, a primary power supply supplied from the power supply device 3 to each mounted device; 5, an attitude control device for properly maintaining the attitude of the satellite; Is a control command signal output from the attitude control device 5, 7 is a magnetic torquer control device for controlling the magnetic torquer according to the control command signal 6 output from the attitude control device 5, and 8 is a magnetic torquer control device that controls the magnetic torquer. Control current 9 to output the control current 8
It is a magnetic torquer operated by.

FIG. 4 is a block diagram of the inside of a magnetic torquer control device showing the prior art of the magnetic torquer control device 7 configured and used as described above. Reference numeral 10 denotes a voltage of the primary power supply 4 for controlling the magnetic torquer 9. DC to convert to secondary voltage for
The DC / DC converter 11 is an on / off circuit which is configured by a relay or a transistor and turns on / off the secondary voltage of the DC / DC converter 10 with respect to the magnetic torquer 9 in accordance with the control command signal 6 output from the attitude control device 5. .

Next, the operation will be described. The solar cell panel 1 is a panel on which a solar cell for converting sunlight into electricity is attached, and generates electric power required by the artificial satellite. The power 2 generated by the solar cell panel 1 is supplied to the power supply 3 so that the voltage does not change with the intensity of sunlight incident on the solar cell panel 1 or the power consumption of each device mounted on the artificial satellite. Thus, a stable voltage is supplied to each device as a primary power supply 4. The attitude control device 5 detects the position of the artificial satellite by observing the position of the sun or the earth, etc. When the satellite deviates from the original correct attitude, a control command signal 6 is sent to the magnetic torquer controller 7 to return the satellite to the original attitude, and the magnetic torquer controller 7 controls the magnetic torquer 9 in accordance with the control command signal 6 from the attitude controller 5. Control. The magnetic torquer 9 generates a magnetic moment by the control current 8 output from the magnetic torquer control device 7 and controls the attitude of the satellite by interaction with the earth magnetism. 4, the voltage of the primary power supply 4 is normally in the range of about 50 V to 52 V when the solar cell panel 1 is exposed to sunlight, Panel 1
When no sunlight is applied, power is supplied from the storage battery inside the power supply device 3 so that the power is in the range of about 32 V to about 50 V. On the other hand, the voltage for controlling the magnetic torquer 9 is a lower constant voltage. Therefore, the magnetic torquer control device 7 is provided with the DC / DC converter 10 and is always operating to convert the voltage of the primary power supply 4 to a secondary voltage for controlling the magnetic torquer 9. For this reason, the DC / DC converter 10 consumes power even when there is no request for attitude control of the satellite. When the attitude of the satellite deviates from the normal position and returns to the original correct attitude, the attitude control device 5 sends the magnetic torquer 9
Is instructed to the ON / OFF circuit 11 of the magnetic torquer control device 7 for controlling the control. ON / OFF circuit 11
Is a DC / DC converter 1 based on the control command signal 6.
By connecting and disconnecting the secondary voltage of 0 with a relay or a switch by a transistor, the control current 8 is supplied to the magnetic torquer 9.
Output as When the control current 8 flows through the magnetic torquer 9 to generate a magnetic moment, the attitude of the satellite changes due to the interaction with the earth magnetism, and the attitude of the satellite is correctly maintained. The present invention relates to the magnetic torquer control device 7 operated as described above.

[0005]

Since the conventional magnetic torquer control device is configured as described above, the DC / DC converter always stands by in the operating state irrespective of the presence or absence of the magnetic torquer control request. Therefore, the power consumed by the DC / DC converter itself is lost, and the power is wasted. Further, since the magnetic torquer is controlled by the constant voltage of the DC / DC converter, there is a problem that the current value supplied to the magnetic torquer changes according to the temperature of the magnetic torquer, and the magnetic moment changes. Further, since the DC / DC converter is mounted, the size and shape of the magnetic torquer control device are large and heavy.

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and the temperature of a magnetic torquer changes with the exception of a DC / DC converter connected to a primary power supply of a magnetic torquer control device. Another object of the present invention is to control the current supplied to the magnetic torquer to a constant value and to make the magnetic torquer control device small and light to facilitate the mounting on a satellite.

[0007]

According to a first aspect of the present invention, there is provided a magnetic torquer control device for an artificial satellite, wherein a control current for supplying an output of a switch circuit for turning on / off a primary power supply in accordance with a control command signal of an attitude control device to the magnetic torquer is provided. The control current is output to the magnetic torquer by a switching circuit that switches according to a pulse width signal output from a pulse width modulation circuit by a control current feedback signal detected by a control current detector so as to be constant.

Further, in the magnetic torquer control device for a satellite according to the second invention, the pulse width modulation circuit is controlled by the control current feedback signal detected by the control current detector so that the control current supplied to the magnetic torquer becomes constant. A switching circuit that performs switching by AND operation of two signals of a pulse width signal as an output and a control command signal output from the attitude control device is operated to output a control current to a magnetic torquer.

[0009]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a block diagram of a magnetic torquer control device according to a first embodiment of the present invention. In FIG. 1, reference numeral 4 denotes a primary power source, 5 denotes an attitude control device, 6 denotes a control command signal output from the attitude control device 5, 7 is a magnetic torquer control device, 8 is a control current output by the magnetic torquer control device 7 for controlling the magnetic torquer, 9 is a magnetic torquer operated by the control current 8, 11 is an attitude control device 5
An on / off circuit for turning on / off the primary power supply 4 in accordance with the control command signal 6 generated by the control circuit; a pulse width modulation circuit for detecting a voltage of the primary power supply and generating a pulse width signal inversely proportional to the voltage; A pulse width signal generated by 12; a switching circuit 14 for generating a control current 8 for controlling the magnetic torquer 9 by rapidly switching the output of the on / off circuit 11 with a transistor in accordance with the pulse width signal 13 output from the pulse width modulation circuit 12; Reference numeral 15 denotes a control current detector for detecting the control current 8, and 16 denotes a control current feedback signal detected by the control current detector 15.

Next, the operation will be described. Usually, the voltage of the primary power supply 4 is in the range of about 32 V to about 52 V as described in the description of the conventional magnetic torquer control device, and therefore, the constant voltage which is a control voltage for controlling the normal magnetic torquer 9 is used. And the control current 8 supplied to the magnetic torquer 9 needs to be constant. In FIG. 1, the pulse width modulation circuit 12 of the magnetic torquer control device 7 includes a control current detector 1
The control current 8 detected in step 5 is controlled by the control current feedback signal 16 so that the output pulse width is reduced when the control current 8 is large, and the pulse width is widened when the control current 8 is small. Therefore, the pulse width modulation circuit 1
2 generates a pulse width signal 13 so as to make the control current 8 constant. On the other hand, the on / off circuit 11 turns on / off the primary power supply 4 by a circuit such as a relay or a transistor according to an instruction of the control command signal 6 generated by the attitude control device 5. The output of the ON / OFF circuit 11 is output to the magnetic torquer 9 as the control current 8 controlled by the switching circuit 14 to be constant by the pulse width signal 13 output from the pulse width modulation circuit 12. In other words, the magnetic torquer 9 can be stably controlled because it is supplied to the magnetic torquer 9 as the control current 8 that is kept constant irrespective of the voltage change due to the voltage change of the primary power supply 4 and the temperature change of the magnetic torquer 9. . The magnetic torquer 9
Is operated by the control signal 8 output from the switching circuit 14 with a constant control current 8 according to the pulse width signal 13 output from the pulse width modulation circuit 12, so that the control command signal 6 generated by the attitude control device 5 as in the prior art. Works according to
Accordingly, the magnetic torquer 9 operates according to the control command signal 6 required by the attitude control device 5 to generate a magnetic moment, so that the attitude of the artificial satellite changes due to the interaction with the earth magnetism, and the attitude of the artificial satellite is correctly maintained. .

Embodiment 2 FIG. 2 is a block diagram of a magnetic torquer control device according to a second embodiment of the present invention. In FIG. 2, reference numeral 4 denotes a primary power source, 5 denotes an attitude control device, 6 denotes a control command signal output from the attitude control device 5, 7 Is a magnetic torquer controller, 8 is a control current output by the magnetic torquer controller 7 for controlling the magnetic torquer, 9 is a magnetic torquer operated by the control current 8, and 12 is a voltage detected by detecting the voltage of the primary power supply 4. A pulse width modulation circuit that generates an inversely proportional pulse width signal 13, 13 is a pulse width signal generated by the pulse width modulation circuit 12, 15 is a control current detector that detects the control current 8, and 16 is a detection from the control current detector 15 The control current feedback signal 17 is a pulse width signal 13 output from the pulse width modulation circuit 12 and a control command signal 6 for turning on / off the magnetic torquer control generated by the attitude control device 5. 2 of
An AND circuit for producing an AND of two signals, 14 is an AND circuit
This is a switching circuit for generating a control current 8 for controlling the magnetic torquer 9 by high-speed switching of the primary power supply 4 by a transistor in accordance with a pulse width signal 13 output from a circuit 17.

Next, the operation will be described. The pulse width modulation circuit 12 of the magnetic torquer control device 7 includes the control current detector 1
The control current 8 detected in step 5 is controlled by the control current feedback signal 16 so that the output pulse width is reduced when the control current 8 is large, and the pulse width is widened when the control current 8 is small. Therefore, the pulse width modulation circuit 1
2 generates a pulse width signal 13 so as to make the control current 8 constant. The AND circuit 17 generates an AND signal of two signals of a pulse width signal 13 output from the pulse width modulation circuit 12 and a control command signal 6 for turning on / off the magnetic torquer control generated by the attitude control device 5. That is, the pulse width signal 13 is output to the switching circuit 14 only when the control command signal 6 is present. The switching circuit 14 outputs to the magnetic torquer 9 as the control current 8 controlled to be constant by the pulse width signal 13 output from the pulse width modulation circuit 12 which is the output of the AND circuit 17. In other words, the magnetic torquer 9 can be stably controlled because it is supplied to the magnetic torquer 9 as the control current 8 that is kept constant irrespective of the voltage change due to the voltage change of the primary power supply 4 and the temperature change of the magnetic torquer 9. . The operation of the magnetic torquer 9 is controlled by the switching circuit 14.
Operates at a constant control current 8 according to the pulse width signal 13 output from the pulse width modulation circuit 12, so that it operates according to the control command signal 6 generated by the attitude control device 5 as in the conventional case. Accordingly, the magnetic torquer 9 operates according to the control command signal 6 required by the attitude control device 5 to generate a magnetic moment, so that the attitude of the artificial satellite changes due to the interaction with the earth magnetism, and the attitude of the artificial satellite is correctly maintained. .

[0013]

According to the first aspect of the present invention, a DC / DC which operates constantly and consumes electric power even when the magnetic torquer is not controlled.
No converter is required, and DC / DC
Since there is no DC converter, wasteful power is not consumed compared to the conventional magnetic torquer control device, and the magnetic torquer is controlled with a constant current so that the magnetic torquer can be controlled stably even when the temperature of the magnetic torquer changes. And DC /
Since the DC converter is not required, the size and weight of the magnetic torquer control device can be reduced, and the mountability on the artificial satellite is facilitated.

Also, in the second invention, a DC / DC converter that operates constantly and consumes power even when the magnetic torquer is not controlled is unnecessary as in the first invention. Since there is no converter, no wasteful power is consumed compared to the conventional magnetic torquer control device, and since the magnetic torquer is controlled with a constant current, the magnetic torquer can be controlled stably even when the temperature of the magnetic torquer changes. And the on / off circuit can be omitted, and DC
The size and weight of the magnetic torquer control device can be further reduced, including the unnecessary portion of the / DC converter, and the mountability on the artificial satellite is facilitated.

[Brief description of the drawings]

FIG. 1 is a block diagram showing Embodiment 1 of a magnetic torquer control device for an artificial satellite according to the present invention.

FIG. 2 is a block diagram showing Embodiment 2 of a magnetic torquer control device for an artificial satellite according to the present invention.

FIG. 3 schematically shows an example of use of a conventional attitude control device, a magnetic torquer control device, and a magnetic torquer used for attitude control of a general artificial satellite.

FIG. 4 is a block diagram showing a configuration of a conventional magnetic torquer control device for artificial satellites.

[Explanation of symbols]

1 solar panel, 2 generated power, 3 power supply, 4
Primary power supply, 5 attitude control device, 6 control command signal, 7
Magnetic torquer controller, 8 control current, 9 magnetic torquer, 10 DC / DC converter, 11 on / off circuit, 12 pulse width modulation circuit, 13 pulse width signal, 1
4 switching circuit, 15 control current detector, 16
Control current feedback signal, 17 AND circuit.

Claims (2)

[Claims] An on-off circuit for supplying a primary power supply to a magnetic torquer according to a magnetic torquer control command signal input from an attitude control device, and a current supplied to the magnetic torquer. A pulse width modulation circuit that generates a pulse width signal for operating the magnetic torquer by detecting the pulse width modulation circuit, and a switching circuit that switches an output of the on / off circuit according to a pulse width signal output from the pulse width modulation circuit, A magnetic torquer control device for an artificial satellite, wherein a current supplied to the magnetic torquer is feedback-controlled. 2. A magnetic torquer control device mounted on an artificial satellite, comprising: a pulse width modulation circuit for detecting a current supplied to the magnetic torquer to generate a pulse width signal for operating the magnetic torquer; and an attitude control device. An AND circuit for generating an AND signal between the input magnetic torquer control command signal and the pulse width signal output from the pulse width modulation circuit;
A switching circuit for switching a primary power supply in accordance with a pulse width signal output from the AND circuit;
A magnetic torquer control device for an artificial satellite, wherein a current supplied to the magnetic torquer is feedback-controlled.