JPH051865U - Ion engine flow regulator controller for satellite - Google Patents

Abstract

(57) [Abstract] [Purpose] A single power supply supplies a stable power supply voltage to a plurality of flow rate regulator drive circuits to stably control the attitude of the satellite. [Structure] The voltage drop across the flow rate regulator caused by applying a flow rate regulator drive signal applied to the flow rate regulator group to the flow rate regulator is fed back to the logic operation circuit as a feedback signal, and the power supply is controlled by the logic operation circuit. [Effect] It is possible to supply a constant flow rate regulator drive signal to the flow rate regulator group.

Description

[Detailed description of the device]

[0001]

[Industrial applications]

 In this device, a plurality of flow rate regulator drive circuits and flow rate regulator groups are connected to one power supply output terminal, and the power supply is controlled using a logical operation circuit for the load fluctuation of each flow rate regulator group, and the flow rate is controlled. The present invention relates to a flow regulator controller for an ion engine mounted on a satellite that supplies a stable voltage to a regulator drive circuit.

[0002]

[Prior Art]

First, we explain the conventional flow regulator controller for an ion engine mounted on a satellite. FIG. 3 is a diagram showing a conventional flow controller for an ion engine mounted on a satellite, in which 1A to 1C are a first power source, a second power source, a third power source, and 2A to 2C, respectively. Are the first flow rate regulator drive circuit, the second flow rate regulator drive circuit, 3A to 3C are the first flow rate regulator group, the second flow rate regulator group, and the third flow rate regulator group, respectively. A is a first power supply line supplied from the first power supply 1A to the first flow rate regulator drive circuit 2A, and 4B is a second power supply line supplied from the second power source 1B to the flow rate regulator drive circuit 2B. 4C is the first drive signal supplied from the third power supply 1C to the third flow rate regulator drive circuit 2A, and 5B is supplied from the second flow rate regulator drive circuit 2B to the second flow rate regulator group 3B. The second drive signal 5C that is generated is the third flow rate adjustment signal from the third flow rate regulator drive circuit 2C. Third drive signal supplied to the vessel 3C, V _B denotes a bus line.

In such a conventional configuration, a power supply current is sent from each power supply to each flow rate regulator drive circuit so that a certain surface of the artificial satellite always faces the earth with respect to the attitude of the satellite. The flow regulator drive circuit supplies a flow regulator drive signal to each flow regulator group according to the power supply current to open the flow regulator to adjust the flow of xenon gas and adjust the injection of xenon gas. You can

[0004]

[Problems to be solved by the device]

The above-mentioned conventional flow regulator controller for an ion engine mounted on a satellite has a flow regulator drive circuit 2A to 2C for opening and closing the flow regulator so that the attitude of the satellite always faces a certain plane of the satellite with respect to the earth. Because it needed a power supply that met the requirements of the above, each flow rate regulator drive circuit had one power supply. Therefore, since the power supplies 1A to 1C receive the change of the power supply bus line V _B , the flow regulator drive circuits 2A to 2C are hardly affected. Moreover, each power supply and the flow rate regulator drive circuit are configured in a pair, and the power source absorbs the voltage variation in response to the voltage variation of the flow rate regulator drive circuit, thus affecting other power sources and the flow rate regulator drive circuit. There was no advantage. However, the number of flow rate regulators that can be driven by one flow rate regulator drive circuit is limited, and the required number of flow rate regulators increases, and the more flow rate regulator drive circuits that are installed in the satellite, the more power is required. A lot of them are needed, and as a result, there are drawbacks such as an increase in the number of parts, an increase in failures due to an increase in parts, and an increase in weight due to the use of many power supplies. The purpose of artificial satellites is to have a long life, and many communication devices can be installed. However, if the above-mentioned drawbacks are not satisfied, it is difficult to fulfill the mission of artificial satellites. Therefore, the conventional flow controller for ion engines mounted on artificial satellites has a large number of parts, in addition to an increase in power loss due to an increase in types of power sources, an increase in weight, an increase in the area used, as the size of the artificial satellite increases. There were problems such as the decrease in reliability due to increase in number and circuit complexity.

The present invention has been made in order to solve the above problems, and uses a logical operation circuit to supply a stable power supply voltage to a plurality of flow rate regulator drive circuits connected to one power supply output. It is an object of the present invention to provide a flow regulator controller for an ion engine mounted on a satellite that enables supply.

[0006]

[Means for Solving the Problems]

 In this invention, the flow regulator driving signal applied to the flow regulator group causes a voltage drop that changes in various ways according to the change in the load condition of the flow regulator, and the voltage value is used as a feedback signal to perform a logical operation in the satellite. It is fed back to the circuit and the power supply is controlled by a logic operation circuit.

[0007]

[Action]

 In this invention, the voltage value between the input of the flow rate regulator and the ground is input to the logical operation circuit, and an appropriate level amount is fed back to the power supply according to the voltage of the input of the flow rate regulator group that changes with load fluctuation. , Control the output of the power supply to the operating voltage of the flow rate regulator.

[0008]

【Example】

Example 1. Figure 1 is a block diagram showing an embodiment of this invention, 2A～5C and V _B are of identical upper Symbol conventional device. 6 is a power source, 7A to 7C are power source outputs for connecting the power source output end and the first flow rate regulator drive circuit 2A to the third flow rate regulator drive circuit 2C, and 8A to 8C are the first flow rate regulator group 3A. ~ Feedback signal for connecting the third flow rate regulator group 3C and the logic operation circuit, and 10 is a power supply control signal for connecting the logic operation circuit 9 and the power supply 6. The control signal 14B for the switch S1, the control signal 14C for the switch S2, and the control signal 14D for the switch S3 are the flow rate depending on the load fluctuations of the flow rate regulator groups 3A, 3B, 3C. Since the input voltage of the regulator group fluctuates, the switches S1, S2, S3 are turned on and off so as to minimize the fluctuation range, and the voltage supplied to the flow rate regulator drive circuit is stabilized. Further, when the flow rate regulator groups 3A, 3B, 3C are short-circuited or overloaded, the switches S1, S2, S3 are turned off to stop the power supply to the flow rate regulator drive circuits 2A to 2C, and at the same time, the pre-regulator 11 The pre-regulator control signal 14A is generated so as to turn off the output of.

The power supply 6 has a multi-output end, and the flow rate adjuster drive circuits 2A to 2C are connected to the output end, and each flow rate adjuster drive circuit drives a corresponding flow rate adjuster group 3A to 3C. , The logical operation circuit 9 detects the change of each voltage of the flow rate regulator group with the feedback signals 8A to 8C, detects the change of the feedback signals 8A to 8C, feeds back the appropriate level amount to the power source 6, and outputs the output of the power source 6. Control so that the flow regulator operating voltage is reached. FIG. 2 shows the inside of the power supply 6 in detail. 2A to 2C and 9 are the same as in FIG. Reference numeral 11 is a pre-regulator, 13A to 13C are first to third filters, S1 is a switch for connecting and disconnecting between the output circuit 12 and the first filter 13A, and S2 is between the output circuit 12 and the second filter 13B. S3 is a switch for connecting and disconnecting, S3 is a switch for connecting and disconnecting between the output circuit 12 and the third filter 13C, 14A is a pre-regulator control signal supplied from the logic operation circuit 9 to the pre-regulator 11, and 14B is a switch. S1 is a control signal, 14C is a switch S2 control signal, and 14D is a switch S3 control signal. The pre-regulator control signal 14A from the logical operation circuit 9 optimizes the operation efficiency of the pre-regulator 11 and at the same time the bus line V_B  ^{The output of the pre-regulator 11 is made constant with respect to the change of.}

Note that the present invention has various modifications in hardware implementation, and a xenon gas control system for an ion engine using a zero momentum three-axis attitude control system and an ion engine using a bias momentum three-axis attitude control system. There is an advantage that it can be applied to the xenon gas control system.

[0011]

[Effect of the device]

 As explained above, the present invention uses a logical operation circuit for a power source, which tends to become more complicated as the size of an artificial satellite increases, and has a control function increased from the conventional one and is simplified as a whole. As a result, a constant flow rate regulator drive signal can be supplied to the flow rate regulator group, and a small flow rate regulator control device having high performance and high reliability can be realized.

[Brief description of drawings]

FIG. 1 is a block diagram showing a flow controller of an ion engine for an artificial satellite according to an embodiment of the present invention.

FIG. 2 is a block diagram showing the internal details of a power supply that constitutes the present invention.

FIG. 3 is a block diagram showing a conventional flow regulator controller for an ion engine mounted on a satellite.

[Explanation of symbols]

 2A 1st flow rate regulator drive circuit 2B 2nd flow rate regulator drive circuit 2C 3rd flow rate regulator drive circuit 3A 1st flow rate regulator group 3B 2nd flow rate regulator group 3C 3rd flow rate regulator Group 5A 1st drive signal 5B 2nd drive signal 5C 3rd drive signal 6 Power supply 7A 1st power supply output 7B 2nd power supply output 7C 3rd power supply output 8A 1st feedback signal 8B 2nd feedback Signal 8C Third feedback signal 9 Logical operation circuit 10 Power supply control signal

Claims (1)

[Claims for utility model registration] [Claim 1] A plurality of flow rate regulator groups arranged in parallel for injecting xenon gas by adjusting the flow rate of xenon gas in an ion engine mounted on a satellite and the attitude of the satellite A plurality of flow rate regulator drive circuits for controlling the opening and closing of the plurality of flow rate regulator groups so that a certain plane of the satellite always faces the earth, and an output terminal connected in series to the satellite battery. And a logic operation circuit that supplies a power supply control signal to the power source so that the drive signal to the flow rate regulator group has a preset flow rate regulator operating voltage. A flow controller for an ion engine for an artificial satellite, comprising: