JP2001095062A - Command reception circuit for astronautical device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a command reception circuit for astromautical device, which has a simple constitution and can reduce number of item parts, and can be made small-sized and light-weight. SOLUTION: A first electronic circuit 10, to which an interface condition according to a command signal is set, is provided with a non-latch relay 14, and constant voltage circuits 16 and 17 are provided which generate corresponding constant voltages to second electronic circuits 12-1 to 12-n and 13-1 to 13-m which differ in interface conditions. Power is supplied from a bus line 15 to constant voltage circuits 16 and 17 via the non-latch relay 14 only in the period, when the relay 14 is temporarily turned on in accordance with the command signal inputted to the first electronic circuit 10, and then constant voltages meeting interface conditions are applied to latch relays 18 and 19 in second electronic circuits 12-1 to 12-n and 13-1 to 13-m, and relays 18 and 19 are turned on to drive circuits 12-1 to 12-n and 13-1 to 13-m.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a command receiving circuit used in a space-borne device of a spacecraft such as an artificial satellite whose operation is controlled in response to a command signal from a ground station or the like.

[0002]

2. Description of the Related Art Conventionally, as shown in FIG. 3, a command receiving circuit used for a space-borne device of a spacecraft such as an artificial satellite, as shown in FIG. The first electronic circuit 2 having a width of 30 msec and a current consumption of 90 mA or less is set.
And a non-latch relay 4 built in the first electronic circuit 2 and a DC-DC converter 5. The input of the DC-DC converter 5 is connected to a bus line 6 serving as a power source of the spacecraft, and converts a DC voltage supplied from the bus line 6 into a predetermined stable voltage.

The non-latch relay 4 in the first electronic circuit 2
Is turned on in response to, for example, a command signal that satisfies interface conditions is input to the first electronic circuit 2 from a RIU (remote interface unit).

[0004] One of the relay contacts of the non-latch relay 4 is connected to the output of the DC-DC converter 5, and when turned on, the power supplied from the converter 5 is supplied to the second electronic circuit via the other of the relay contacts. Output to 3-1 to 3-n. The second electronic circuits 3-1 to 3-n have the same interface conditions as the first electronic circuit 2 with respect to command signals. However, due to the limitation of the maximum current consumption in the above interface conditions, it is not possible to drive all the electronic circuits 2, 3-1 to 3-n with a command signal from the RIU.

Therefore, the first signal is issued by a command signal from the RIU.
(The non-latch relay 4 therein) is driven, and a voltage matching the interface conditions is applied from the DC-DC converter 5 to the second electronic circuits 3-1 to 3-n accordingly. With this configuration, the second electronic circuits 3-1 to 3-n can be driven as described below.

First, a latch relay 7 (shown only in the electronic circuit 3-1 in FIG. 2 for convenience of illustration) is built in the second electronic circuits 3-1 to 3-n. The latch relay 7 is connected to the DC-DC converter 5 via the non-latch relay 4. As a result, the latch relay 7 is turned on when a voltage is applied from the DC-DC converter 5 in response to the turning on of the non-latch relay 4. Then, the second
Of the electronic circuits 3-1 to 3-n are driven substantially simultaneously.

As described above, in the command receiving circuit having the configuration shown in FIG. 2, only the non-latch relay 4 (relay means) built in the first electronic circuit 2 is driven by the input command signal. From the converter 5 to the second electronic circuit 3
By applying a voltage that matches the interface conditions to -1 to 3-n, the second electronic circuits 3-1 to 3-n can also be driven.

[0008]

However, in a conventional command receiving circuit of a space-borne device, in order to satisfy the interface condition of the command signal, an electronic circuit (relay means built in the electronic circuit driven in response to the command signal) is used. ) To supply power to other electronic circuits via
Because of the provision of the converter, the following problems were encountered. In other words, the DC-DC converter has a relatively large number of parts and requires a control system for controlling the operation of the converter, which complicates the configuration and is large and heavy.

[0009] In recent years, with the diversification of electronic circuits provided in space-borne equipment, interface conditions often differ depending on the electronic circuit. If electronic circuits with different driving voltages in the interface conditions are mounted, it is necessary to group the electronic circuits at least for each driving voltage and prepare a DC-DC converter with a different output voltage for each group. The problem becomes more serious.

[0010] Such problems have been raised in recent space development fields. Due to the demand for diversification of operation, high-density mounting of space-borne equipment is being planned, and there is a demand for small and lightweight space-borne equipment, which is one of the important issues. I have.

SUMMARY OF THE INVENTION The present invention has been made in view of the above circumstances, and has as its object to provide a command receiving circuit for a space-borne device which has a simple configuration, can reduce the number of parts, and can be reduced in size and weight. .

[0012]

According to the present invention, a command receiving circuit of a space-borne device according to the present invention comprises a first electronic circuit for setting an interface condition according to a command signal and a bus line serving as a power source of a spacecraft. Receiving the power supply, the interface condition according to the command signal is set.
A constant voltage circuit for generating a constant voltage that matches the interface condition for driving the electronic circuit, and temporarily controlling switching by a command signal that is built in the first electronic circuit and that is input to the electronic circuit. And relay means for supplying power from the bus line to the constant voltage circuit only during that period.

In such a configuration, for example, RIU
When a command signal is input to the first electronic circuit via the switch, the relay means in the first electronic circuit is switched and controlled in response to the command signal, and is controlled during the period (for example, determined by the pulse width of the command signal). The power from the bus line constituting the power source of the spacecraft is supplied to the constant voltage circuit as the power source of the constant voltage circuit only during the ON period of the relay means). Then, a constant voltage is applied from the constant voltage circuit to the second electronic circuit almost simultaneously, and the second electronic circuit is driven. As a result, efficient and effective use of the bus line of the power source of the spacecraft is realized, and it is not necessary to provide a dedicated DC-DC converter as in the related art as a driving power source of the second electronic circuit. Therefore, it is possible to reduce the number of parts and promote downsizing and weight reduction.

The above configuration is applicable when at least the drive voltage in the interface conditions of each second electronic circuit is common. However, in recent years, with the diversification of electronic circuits provided in space-borne equipment, the drive voltage during interface conditions often differs depending on the electronic circuit.

Therefore, according to the present invention, a constant voltage circuit is provided for each group of the second electronic circuits classified according to at least a difference in drive voltage in the interface condition, and the constant voltage circuit is provided by a command signal input to the first electronic circuit. When the switching of the relay means in the electronic circuit is controlled, the power from the bus line is supplied to the constant voltage circuit of each group only during that period, and the second voltage of the corresponding group from each constant voltage circuit is set from each constant voltage circuit. It is also characterized in that the electronic circuit is configured to apply a constant voltage that matches the drive voltage in the interface conditions of the electronic circuit.

In such a configuration, a constant voltage circuit provided for each group having a different driving voltage is used under the constraint of the interface condition for the command signal.
Since the electronic circuits in the corresponding group can be driven, it is possible to reduce the number of components and promote the reduction in size and weight while dealing with the diversification of electronic circuits provided in the space-borne equipment.

[0017]

Embodiments of the present invention will be described below with reference to the drawings. FIG. 1 shows a configuration centering on a command receiving circuit of a space-borne device according to an embodiment of the present invention.

In FIG. 1, the first electronic circuit 10 includes a main body (a main body of a space-borne device) 11 of a spacecraft such as an artificial satellite, and other second electronic circuits 12-1 to 12-.
n, 13-1 to 13-m.

The first electronic circuit 10 has an interface condition (for example, a pulse width of 30 msec) for the command signal.
c, the current consumption is 90 mA or less). For example, a command signal of MAX 90 mA and a voltage of 26 V that matches the above interface conditions is input to the electronic circuit 10 via the RIU. On the other hand, the second electronic circuits 12-1 to 12-1 to
12-n and 13-1 to 13-m are different from each other in at least the drive voltage in the interface condition.
The 2-n driving voltage is, for example, the same as that of the first electronic circuit 10.
6V and the drive voltage of the electronic circuits 13-1 to 13-n is 18V.

The first electronic circuit 10 is provided with a non-latch relay 1 which is turned on / off by an input command signal.
Four. When a command signal is input to the first electronic circuit 10, the non-latch relay 14 uses the command signal (current consumption is 90 mA or less) as an interface condition and sets the command signal to a high level (first
Is turned on only for a period (here, 30 msec).

The non-latch relay 14 includes a relay contact 14
1,142. One of the relay contacts 141 and 142 is connected to a power source of the spacecraft, for example, 50V.
142 is connected to the DC voltage bus line 15,
Are the constant voltage circuit 16 and the second electronic circuits 13-1 to 13-n corresponding to the second electronic circuits 12-1 to 12-n (that is, the group in which the drive voltage in the interface condition is 26 V).
(That is, a group in which the drive voltage in the interface condition is 18 V).

The constant voltage circuit 16 is composed of a series circuit of a current limiting resistor R1 and a 26V zener diode D1, and is supplied from the bus line 15 in response to the ON of the non-latch relay 14 in the first electronic circuit 10. The 50 V power supply generates a constant voltage of 26 V (at the connection point between the resistor R1 and the Zener diode D1) only during the ON period of the relay 14. On the other hand, the constant voltage circuit 17 includes a current limiting resistor R
And a non-latch relay 14 in the first electronic circuit 10 which is composed of a series circuit of
Is turned on by the 50V power supply supplied from the bus line 15 during the ON period of the relay 14 (the resistor R2
Constant voltage 18 at the connection point between
Generate V.

The constant voltage 2 generated by the constant voltage circuit 16
6V is applied to a latch relay 18 (only the electronic circuit 12-1 is shown for convenience in the drawing) built in the second electronic circuits 12-1 to 12-n, and a constant voltage generated by a constant voltage circuit 17 is applied. 18V is applied to a latch relay 19 (only the electronic circuit 13-1 is shown in the drawing for convenience) built in the second electronic circuits 13-1 to 13-m.

Electronic circuits 12-1 to 12-n, 13-1 to 13-m
The latching relays 18 and 19 have driving voltages of 26 V and 18 V, respectively, which are one of the interface conditions.
26V, 18V voltages applied only from the constant voltage circuits 16 and 17 during the ON operation of the non-latch relay 14 in the electronic circuit 10 based on the command signal (here, the ON operation during a period of 30 msec). Is turned on. At this time, the bus line serving as the power source of the constant voltage circuits 16 and 17 has a very short pulse width of the command signal input to the electronic circuit 10 of about 30 msec. Since the operation period is as short as about 30 msec, it does not adversely affect the function of the spacecraft as a power source.

Now, the electronic circuits 12-1 to 12-n, 13-1 to
13-m is the built-in latch relay 18, 19 as described above.
Is turned on, power can be supplied from a power supply circuit (not shown) using the bus line 15 as a power source.
It is driven almost simultaneously with 0. Here, the electronic circuits 12-1 to 12-12
-n, 13-1 to 13-m, the on-states of the latch relays 18 and 19 are, for example, the electronic circuits 12-1 to 12-n and 13-1 to 1
3-m is held until the OFF command is output from itself.

As described above, in the present embodiment, the second electronic circuits 12-1 to 12-n and 13-1 to 13-m arranged in the space-borne equipment body 11 together with the first electronic circuit 10 are provided. Is
When a command signal is input to the first electronic circuit 10, the signal is set in conjunction with a temporary ON operation (determined by the pulse width of the command signal) of the non-latch relay 14 in the electronic circuit 10 in response to the command signal. Built-in latch relay 1 with voltage of 26V, 18V supplied from voltage circuits 16, 17
8 and 19 are turned on, and drive control is performed almost simultaneously.

That is, when the command signal is input to the first electronic circuit 10, the built-in non-latch relay 14 is turned on, and the command receiving circuit of the space-borne device according to the present embodiment turns on the non-latch relay 14. 30ms
Only in c), the constant voltage circuits 16 and 17 receive the power supply from the bus line 15, and the second electronic circuits 12-1 to 12-n,
Voltages (26 V, 18 V) meeting the interface conditions of 13-1 to 13-m are applied to the electronic circuits 12-1 to 12-n, 1
The electronic circuits 12-1 to 12-n and 13-1 to 13-m are turned on by being applied to the latch relays 18 and 19 of 3-1 to 13-m.
13-m is configured to be driven.

According to this, the effective and effective use of the bus line 15 as a power source of the spacecraft is realized, and the non-latch relay 14 built in the first electronic circuit 10 is realized.
Of the second electronic circuits 12-1 to 12-n, 13-1
By using the constant voltage circuits 16 and 17 as voltage sources for the built-in latch relays 18 and 19 in the １３13-m, it is not necessary to provide a dedicated DC-DC converter as in the related art, so that the number of parts can be reduced. Therefore, the miniaturization and weight reduction can be easily promoted.

Further, like the electronic circuits 12-1 to 12-n and the electronic circuits 13-1 to 13-m, the built-in latch relays 18,
Even if the drive voltage of the 19th circuit (as one of the interface conditions) is different, the second group of electronic circuits having different drive voltages (here, the electronic circuits 12-1 to 12-n and the electronic circuit 1
For each 3-1 to 13-m), it can be handled simply by preparing a constant voltage circuit with a simple configuration that outputs the corresponding voltage, and the versatility can be improved. The handleability including the design can be improved.

The present invention is not limited to the above embodiment. For example, as a constant voltage circuit, instead of a series circuit of the resistor R and the zener diode D, as shown in FIG.
A constant voltage circuit in which a transistor Tr is connected to the other end of the resistor R may be used. When the constant voltage circuit of FIG. 2 is used, a larger current capacity can be secured by the current amplifying function of the transistor Tr as compared with the constant voltage circuits 16 and 17 in FIG. 1, so that more second electronic circuits are driven. it can. Further, depending on the second electronic circuit (a latch relay built in), instead of the constant voltage circuit, the voltage from the bus line 15 is divided by a series circuit of two resistors, and the divided voltage is divided into the second voltage. It is also possible to use a voltage dividing circuit for applying a voltage to an electronic circuit (a built-in latch relay).

In addition, it goes without saying that the present invention can be variously modified and implemented without departing from the gist thereof.

[0032]

As described above in detail, according to the present invention, a command receiving circuit for a space-borne device which promotes miniaturization and weight reduction by making it possible to reduce the number of components with a simple configuration. Can be provided.

[Brief description of the drawings]

FIG. 1 is a block diagram showing a configuration centering on a command receiving circuit of a space-borne device according to an embodiment of the present invention.

FIG. 2 is a diagram showing a modification of the constant voltage circuit applied to the command receiving circuit.

FIG. 3 is a block diagram mainly showing a command receiving circuit of a conventional space-borne device.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 10 ... 1st electronic circuit 11 ... Space-borne equipment main body 12-1-12-n, 13-1-13-m ... 2nd electronic circuit 14 ... Non-latch relay (relay means) 15 ... Bus lines 16, 17 ... Constant voltage circuit 18, 19 ... Latch relay

Claims (2)

[Claims] A first electronic circuit for setting an interface condition according to a command signal; and a second electronic circuit for receiving power supplied from a bus line serving as a power source of the space vehicle to drive the second electronic circuit. A constant voltage circuit that generates a constant voltage that matches an interface condition of the electronic circuit; and a switching circuit that is built in the first electronic circuit and is temporarily switched and controlled by a command signal input to the electronic circuit.
And a relay means for supplying power from the bus line to the constant voltage circuit during the period. A first electronic circuit for setting an interface condition according to a command signal; and a second electronic circuit group classified by at least a difference in drive voltage in the interface condition,
Receiving power supply from a bus line serving as a power source of the space vehicle, and during that period, the second group in the corresponding group;
A constant voltage circuit for generating a constant voltage that matches an interface condition specific to the group, for driving the electronic circuit of the first electronic circuit; Switching control,
Relay means for supplying power from the bus line to the constant voltage circuit of each of the groups during the period.