JPH1028323A - Power source circuit for equipment mounted on spacecraft - Google Patents

Abstract

PROBLEM TO BE SOLVED: To reduce the number of parts in a power source circuit for equipment mounted on a spacecraft and the size and weight of the circuit by driving another electronic circuit by nearly simultaneously supplying electric power from a battery assembly constituting the power source of a spacecraft by switching and controlling a relay means, in response to the driving of a first electronic circuit, when the first electronic circuit is driven by inputting a command signal. SOLUTION: When a command signal RIU is inputted to a first electronic circuit 10, a non-latch relay 13 is turned on, and desired electric power meeting the interface condition of the signal RIU is supplied to a latch-relay 15 from a battery assembly l4, constituting the power source of a spacecraft and other electronic circuits 121-12n, are driven. Therefore, the battery assembly 14, constituting the power source of the spacecraft can be utilized effectively and the number of parts and size and weight of the power source circuit of equipment mounted on the spacecraft can be reduced, because the battery assembly 14 is used as the power sources of the electronic circuits 121-12n.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a power supply 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, a power supply circuit of a space-borne device is shown in FIG.
As shown in the figure, the interface condition (for example, pulse width 30 msec)
c, the current consumption is 90 mA or less) and the first electronic circuit 2 and the plurality of other electronic circuits 31 to 3n are housed and arranged. The non-latch relay 4 is connected to the first electronic circuit 2 among them. This non-latch relay 4 is, for example, R
When a command signal that meets the interface conditions is input to the first electronic circuit 2 from an IU (remote interface unit), the first electronic circuit 2 is turned on in response thereto.

The non-latch relay 4 is connected to an internal power supply circuit 5, and when turned on, the power from the internal power supply circuit 5 is supplied to other electronic circuits 31 to 3n by a latching relay 6 (in FIG. 2, For convenience of illustration, the electronic circuit 31
Only shown in FIG. 2) to turn on the power supply, and to supply the power of the internal power supply circuit 5 to the other plurality of electronic circuits 31 to 3n.
These other electronic circuits 31 to 3n are driven substantially simultaneously.

However, in the power supply circuit of the space-borne device, other electronic circuits 31 to 3 respond to the command signal in order to satisfy the interface condition of the command signal.
Since the internal power supply circuit 5 for supplying power to n is provided, the number of components is relatively large, and a control system for controlling the operation of the internal power supply circuit 5 is required. There is a problem that it is large and heavy.

The problem is that, in the field of recent space development, high density mounting of the spaceborne equipment 1 has been attempted in response to demands for diversification of operations, and the spaceborne equipment 1 has been reduced in size and weight. Is one of the important issues.

[0006]

As described above, the power supply circuit of the conventional space-borne equipment has a problem that the configuration is complicated, large, and heavy. The present invention has been made in view of the above circumstances, and has as its object to provide a power supply circuit for a space-borne device which has a simple configuration and can reduce the number of parts, thereby promoting small size and light weight. Aim.

[0007]

According to the present invention, there is provided a first electronic circuit in which an interface condition corresponding to a command signal is set, and a relay means which is switched and controlled by the command signal input to the first electronic circuit. And a battery assembly that serves as a power source of the spacecraft and supplies and drives a predetermined power to other electronic circuits when the relay means is in an on state. It is composed.

According to the above configuration, when the command signal is input and the first electronic circuit is driven, the switching of the relay means is controlled in response to the command signal, and the battery constituting the power source of the spacecraft is provided. The electric power from the assembly is supplied to other electronic circuits almost simultaneously, and the other electronic circuits are driven. As a result, efficient and efficient use of the battery assembly of the power source of the spacecraft is realized, and the dedicated internal power supply circuit as in the related art is not provided as the power source of other electronic circuits. The number of points can be reduced, and miniaturization and weight reduction can be promoted.

[0009]

Embodiments of the present invention will be described below in detail with reference to the drawings. FIG. 1 shows a power supply circuit of a space-borne device according to an embodiment of the present invention. A first electronic circuit 10 is housed and arranged in a space-borne device main body 11 together with other electronic circuits 121 to 12n. The first electronic circuit 10 is connected to the MAX 9 via the RIU, for example.
A command signal of 0 mA is input.

The first electronic circuit 10 is provided with a non-latch relay 13 that is turned on / off by a command signal. When a command signal is input, the command signal (current consumption is 90 mA or less) is applied to an interface condition. The non-latch relay 13 is turned on. The non-latch relay 13 has one of its relay contacts connected to the battery assembly 1.
4 is connected between the desired cells, and the other end is connected to another electronic circuit 12.
1 to 12n are connected to one end of a latch relay 15 (in FIG. 1, only the electronic circuit 121 is shown for convenience of illustration).

The battery assembly 14 receives power generated by a solar cell paddle (not shown), and is used as a power source for a space vehicle (not shown). This battery assembly 1
The connection position of the non-latch relay 13 with respect to 4 is appropriately set according to the interface condition of the command signal (for example, the MAX current), so as to correspond to the interface condition of various command signals.

When the command signal is input, the non-latch relay 13 outputs a desired voltage (for example, 26) corresponding to the MAX current of the command signal from the battery assembly 14.
V, 18 V, etc.) to the latch relays 15 of the other electronic circuits 121 to 12n to output the electric power of the other electronic circuits 121 to 12n.
12n is driven. At this time, since the pulse width of the command signal is, for example, about 30 msec, the battery assembly 14 does not adversely affect the function as a power source of the spacecraft (not shown).

The latch relay 15 is supplied with desired power corresponding to the current consumption of the command signal from the battery assembly 14 via the non-latch relay 13. Thus, the other electronic circuits 121 to 12n are driven substantially simultaneously with the first electronic circuit 10 using the battery assembly 14 as a power source in response to the command signal.

For example, a large number of the other electronic circuits 121 to 12n are arranged in the space-borne equipment main body 11, and when a command signal is input, the other electronic circuits 121 to 12n substantially operate in conjunction with on / off control of the non-latch relay 13. Similarly, each of the latch relays 15 is turned on, and each of them is drive-controlled.

Note that the battery assembly 14 may simultaneously constitute a power source of a power supply circuit corresponding to different command signals. In this case, the connection position between the cells of the battery assembly 14 is variably set by a command signal in accordance with the power supplied by the driven relay.

As described above, when the command signal is input to the first electronic circuit 10,
When the non-latch relay 13 is turned on, a desired power according to the interface condition of the command signal is supplied from the battery assembly 14 constituting the power source of the spacecraft to the latch relay 15, and the other electronic circuits 121 to 12n are turned on. It was configured to be driven.

According to this, efficient and effective use of the battery assembly 14 of the power source of the spacecraft is realized, and
Since there is no longer a need for a dedicated internal power supply circuit as in the related art as a power source for the other electronic circuits 121 to 12n,
The number of parts can be reduced, and the reduction in size and weight can be easily promoted.

Further, according to this, according to the power supplied by the relay driven by the command signal, the battery assembly 1
4 can be applied to various command signals only by changing the connection position between cells, thereby improving versatility and handling, including the design thereof. It is to be noted that the present invention is not limited to the above-described embodiment, and it goes without saying that various modifications can be made without departing from the spirit of the present invention.

[0019]

As described above in detail, according to the present invention, a power supply circuit of a space-borne device which promotes miniaturization and weight reduction with a simple configuration and a reduction in the number of parts can be achieved. Can be provided.

[Brief description of the drawings]

FIG. 1 is a diagram showing a power supply circuit of a space-borne device according to an embodiment of the present invention.

FIG. 2 is a diagram showing a power supply circuit of a conventional space-borne device.

[Explanation of symbols]

 10: First electronic circuit. 11 Space-borne equipment. 121 to 12n ... other electronic circuits. 13 Non-latching relay. 14. Battery assembly. 15 ... Latch relay.

Claims (4)

[Claims] 1. A first electronic circuit for setting interface conditions according to a command signal, relay means switched and controlled by a command signal input to the first electronic circuit, and a power source for a spacecraft A power supply circuit for a space-borne device, comprising: a battery assembly that supplies and drives predetermined electric power to another electronic circuit when the relay means is on. 2. The battery assembly according to claim 1, wherein electric power generated by a solar cell paddle is stored.
The power circuit of the space-borne equipment described. 3. The battery according to claim 2, wherein the other electronic circuit is selectively connected to a predetermined position between predetermined cells of a battery assembly in accordance with a current consumption of a command signal.
The power circuit of the space-borne equipment described. 4. The relay means has a first relay that is on / off controlled by a command signal, and a second relay that is on / off controlled by power of a battery assembly,
4. The power supply circuit for a space-borne device according to claim 1, wherein the power of the battery assembly is supplied to another electronic circuit in response to the input of the command signal.