JP2000095200A - Satellite testing system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a satellite testing system that does not require much manpower for operation, and eliminates the necessity of procuring the minimum components required for launching a satellite or dedicated testing systems for each satellite, thereby the satellite testing is conducted automatically and efficiently with a shorter period of time. SOLUTION: A satellite 1 interfaces with a ground test unit 2 via a stub cable 100 for the 1553 bus that is connected to a bus interface connector 10 and specified in MIL-STD-1553. By inputting information data such as the addresses of particular components 12 to 15 inside the satellite 1 via the stub cable 100 and the bus interface connector 10, the ground test unit 2 can control the satellite 1 to the same level as a data processing computer 11. The ground test unit 2 sends packet definition files to each of the components 12 to 15 of the satellite 1 via the stub cable 100.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a satellite test system for an artificial satellite, and more particularly to a test method for performing various tests for confirming the satellite state of the artificial satellite on the ground.

[0002]

2. Description of the Related Art Conventionally, as a test method for an artificial satellite, various tests are performed on the ground to confirm the satellite state of the artificial satellite. At this time, the interface between each component mounted on the satellite and the outside is RF (Rad
A telemetry / command interface using an io Frequency (high frequency) method or a baseband method is used.

Here, in the RF system, a baseband signal such as status monitoring (telemetry) of each component mounted on a satellite and a command (command) to each component is converted into an RF signal via a high-frequency device (RF device). Converted,
Each component interfaces with external ground test equipment.

In the baseband system, each component is interfaced with an external ground test device by a baseband signal without interfacing each component with an external ground test device using the RF signal.

FIGS. 8 and 9 show a conventional system for performing various tests for confirming the satellite state of the artificial satellite 3 on the ground. In these figures, the artificial satellite 3 includes a satellite antenna 30, a coaxial cable U-link 31, a baseband interface connector 32, an RF device 33,
A baseband processing device 34 and components 35 and 36 such as a satellite control device, a power supply device, and an imaging device are mounted.

[0006] By connecting the artificial satellite 3 to a ground test apparatus 5 provided with a test antenna 4, various tests for confirming the satellite state of the artificial satellite 3 are performed by the ground test apparatus 5.

In this case, as a method of connecting the artificial satellite 3 and the terrestrial test apparatus 5, (1) a satellite antenna 30 attached to the artificial satellite 3 and a test antenna 4 attached to the terrestrial test apparatus 5 And (2) removing the coaxial cable U-link 31 attached to the artificial satellite 3 and interfacing with the ground test apparatus 5, A method of securing a line 201 (hard line interface) by a hard line and taking an interface; (3) a baseband interface between a test baseband interface connector 32 attached to the artificial satellite 3 and the ground test apparatus 5 using a baseband; A method of securing a line 202 (baseband interface) and taking an interface;
Etc.

[0008]

In the above-mentioned conventional artificial satellite test system, the artificial satellite test is performed using either the RF system or the baseband system, or both. There are many parts that are manually set for commands (commands) and status monitoring (telemetry) to the onboard equipment of the satellite, and there are many unique setting conditions for each satellite, so that the testing equipment for the satellite is shared and testing efficiency is improved. However, it is a difficult part.

That is, in the conventional artificial satellite test method, it is difficult to automate and improve the efficiency of the artificial satellite test and shorten the test period, and it is necessary to procure a test device for each artificial satellite. Also, since there are many devices to be monitored, it is difficult for a small number of people to respond, and the minimum components required to start an artificial satellite are also required.

Accordingly, an object of the present invention is to solve the above-mentioned problems, and to procure a satellite without having to procure the minimum components necessary for starting the satellite and a test device for each satellite. It is an object of the present invention to provide a satellite test system for an artificial satellite which can achieve automation and efficiency of a test, shorten a test period, and can be used by a small number of people.

[0011]

A satellite test system for an artificial satellite according to the present invention is a satellite test system for an artificial satellite equipped with a plurality of components and a data processing computer for controlling the plurality of components. A bi-directional bus for connecting a plurality of components and the data processing computer to each other, an interface connector for connecting an external device to the bi-directional bus, and test information connected to the interface connector and for ground test of the satellite. And a test device for individually outputting to the plurality of components.

That is, in the satellite test system for an artificial satellite according to the present invention, in each component mounted on the artificial satellite, a device specified in MIL-STD-1553 is used as an input / output interface. by this,
This makes it possible to automate the test of the artificial satellite and to share the test device.

That is, by connecting a test device to a data bus for connecting a data processing computer mounted on the inside of a satellite and a plurality of components via a bus interface connector specified in MIL-STD-1553. Since it is possible to connect each component directly from the test apparatus, it becomes easy to automate the satellite test. This makes it easier to shorten the test period of the satellite test, and makes it easier to generalize the test apparatus.

Further, since the test apparatus is connected to each component, it is possible to operate a test by a small number of people, and it is possible to execute test items of only the selected component. Further, since the test input is performed by the packet definition file method of MIL-STD-1553B, anyone can execute the test under the same test condition any number of times.

[0015]

Next, an embodiment of the present invention will be described with reference to the drawings. FIG. 1 is a block diagram showing the configuration of a satellite test system according to one embodiment of the present invention, FIG. 2 is a diagram showing the overall configuration of a satellite test system according to one embodiment of the present invention, and FIG. It is a figure showing peripheral composition of an artificial satellite by one example.

In these figures, the artificial satellite 1 has an MI
A bus interface connector 10 specified by L-STD-1553, a data processing computer 11, and components 12 to 12 such as a satellite control device, a power supply device, and an imaging device.
15, a satellite antenna 16, and an RF device 17.

The artificial satellite 1 is connected to a bus interface connector 10 and interfaces with a ground test apparatus 2 using a stub cable 100 for a 1553 bus specified in MIL-STD-1553. The test of the artificial satellite 1 is performed by sending various test commands for confirming the satellite state of the artificial satellite 1 from the test apparatus 2.

The ground test apparatus 2 is a general-purpose test apparatus having the same function as the data processing computer 11 inside the artificial satellite 1. The ground test apparatus 2 is connected to the satellite 1 via the stub cable 100 and the bus interface connector 10.
By inputting information data such as the addresses of specific internal components 12 to 15, control equivalent to that of the data processing computer 11 can be performed on the artificial satellite 1.

Further, it is possible to obtain necessary satellite data only by turning on specific components 12 to 15 without turning on the entire artificial satellite 1, so that the test can be automated and efficiency can be improved.

Each component 12 to inside the artificial satellite 1
15 is 1553 defined in MIL-STD-1553
The bus interface connector 10 is connected to the bus interface connector 10 by a bus stub cable 101, and the interface with the external ground test apparatus 1 is taken through the bus interface connector 10.

Since the external ground test apparatus 1 has the same function as the data processing computer 11 inside the artificial satellite 1, it is individually connected to the components 12 to 15 without starting the artificial satellite 1 itself. It is possible.

By selecting an arbitrary component 12 to 15 in the external ground test apparatus 1, a telemetry / command test with each of the components 12 to 15 can be performed independently. Further, by scheduling the timing of data collection and the timing of command transmission by the ground test apparatus 1, it is possible to reduce the number of telemetry collection items at the time of testing and to shorten the test period.

In the above configuration, since the configuration of the ground test apparatus 1 is small, the test can be operated by a small number of people. Since the packet definition file is used in the test, the test can be performed under the same conditions no matter how many times the test is performed.

FIG. 4A is a diagram showing an example of the arrangement of the bus interface connector 10 of FIG. 1, and FIG.
Test equipment 2 to the bus interface connector 10
FIG. 3 is a diagram showing a connection example of FIG.

In these figures, the ground test equipment 2 (1
The 553 test apparatus) is connected to the bus interface connector 10 (1553 coupler) of the artificial satellite 1 via the stub cable 100 (1553 stub cable).

FIG. 5 is a diagram showing the format of each word of MIL-STD-1553B used for test input from the ground test apparatus 2 of FIG. FIG. 5A shows MIL-
FIG. 5B shows a format of a command word of STD-1553B, and FIG. 5B shows the format of MIL-STD-1553B.
FIG. 5 is a diagram showing a format of a data word of FIG.
(C) is a figure which shows the format of the status word of MIL-STD-1553B.

In these figures, the command word includes a synchronization bit (SYNC) (3 bits), a root address (RT Addrea) (5 bits), a transmission / reception bit (T / R) (1 bit), and a sub-address. (SUB
Addrea) (5 bits) and data (DATA)
It consists of a number (5 bits) and a parity (1 bit). Here, the number of data is set between 1 and 32, which is the number of data transmitted in the packet definition file.

The data word is a synchronization bit (SYNC).
(3 bits) and data (DATA) (16 bits)
And a parity (1 bit). The status word includes a synchronization bit (SYNC) (3 bits), a root address (RT Addre) (5 bits), and an error message (Error Message) (12).
Bit).

FIG. 6A is a diagram showing the transmission status of the packet definition file shown in FIG. 5, and FIG. 6B is a diagram showing the response transmission status of the packet definition file shown in FIG. In these figures, a command word (TRANSMIT COMMA) is used when transmitting a packet definition file.
ND), a data word (DATA) of the number of data set in the command word, and a status word (STAT)
US) is transmitted.

When transmitting the response of the packet definition file, the command word of the response (RECEIVE COMMAN) is sent.
D) and the command word (TRANSMI
TCOMMAND), a data word (DATA) of the number of data set in the response target command word, a status word (STATUS), and a data word (DATA) of the data number set in the response command word
And a status word (STATUS) are transmitted.

Here, the communication system of MIL-STD-1553B is one system of the telemetry / command bus of the artificial satellite 1, and is a bidirectional bus system. In this case, the command is a command signal that causes the equipment of the artificial satellite 1 to perform necessary operations from the ground or changes the telemetry, and the telemetry is the environment inside the artificial satellite 1, the operating state of the equipment, the artificial satellite (1) Information about the surrounding environment, attitude sensors, and the like.

In the terrestrial test of the artificial satellite 1, an arbitrary signal is input to the artificial satellite 1, and its behavior is confirmed by an output waveform and a signal. Therefore, MIL-STD-1553B
The test input data according to the format specified in (1) is created in advance, and 64-word data is input into the artificial satellite 1 from the ground test apparatus 2 as a block (packet) of file data.

The specifications of MIL-STD-1553B specify the functions of a bus controller and a remote terminal. The bus controller has functions such as command transmission, data transmission / reception, error detection, and status confirmation transferred from the remote terminal. In the above configuration, the function of the data processing computer 11 corresponds to the bus controller.

The remote terminal receives commands from the bus controller, has functions such as transmission and reception of data relating to the specified subaddress, status response to the command, error detection, and the like. The functions of all mounted devices correspond. The identification of each device in the artificial satellite 1 is determined by the address and the subaddress.

FIG. 7 shows an artificial satellite 1 according to an embodiment of the present invention.
6 is a sequence chart showing an example of the test processing of FIG. The test processing of the artificial satellite 1 according to one embodiment of the present invention will be described with reference to FIGS.

At the time of testing the satellite 1 on the ground, the ground test apparatus 2 transmits the satellite 1 via the stub cable 100.
Connected to the bus interface connector 10. After that, the ground test apparatus 2 sends the packet definition file to each of the components 12 to 15 of the artificial satellite 1 via the stub cable 100.

For example, when the ground test apparatus 2 tests the components 12 to 14 in order from the component 12, first, the ground test apparatus 2 sends a packet definition file in which a response confirmation command is inserted to the component 12.

When a response to the response confirmation command is returned from the component 12, the ground test apparatus 2 sends the component 12 a packet definition file in which the ON confirmation command is inserted.

When the ground test apparatus 2 returns a response to the ON confirmation command from the component 12, the ground test apparatus 2 recognizes that the component 12 has started up, and stores a packet definition file in which commands for confirming various functions are inserted. The data is sequentially sent to the component 12 to execute various functional tests.

When various functional tests on the component 12 are completed, the ground test apparatus 2 sends out a packet definition file in which a command for confirming off is inserted into the component 12, and when a response to the command from the component 12 is returned, the component The various functional tests for the next component 13 are completed, and the process proceeds to the various functional tests for the next component 13.

The ground test apparatus 2 sequentially executes the above-described processing operations on the components 13 and 14. When various functional tests on the component 14 are completed, the artificial satellite 1
Is completed (see FIG. 7).

As described above, in each of the components 12 to 15 mounted on the artificial satellite 1, the MIL-STD-1
By using the devices (such as the bus interface connector 10 and the stub cables 100 and 101) specified in 553 for the input / output interface, it is possible to automate the test of the artificial satellite 1 and to share the ground test apparatus 2.

That is, a data bus (stub cable 101) for connecting the data processing computer 11 mounted inside the artificial satellite 1 and the plurality of components 12 to 15
Is connected to the ground test apparatus 2 via the bus interface connector 10 specified in MIL-STD-1553, so that each component 12
15 can be connected, so that the satellite test can be automated. As a result, the test period of the satellite test can be shortened, and the terrestrial test apparatus 2 can be general-purpose.

Further, since the ground test apparatus 2 is connected to each of the components 12 to 15, the test operation can be performed by a small number of people, and the test items of only the selected components 12 to 15 can be performed. Furthermore, the test input is M
Since the test is performed by the packet definition file method of IL-STD-1553B, anyone can execute the test any number of times under the same test conditions.

[0045]

As described above, according to the present invention, in a satellite test system for an artificial satellite equipped with a plurality of components and a data processing computer for controlling the plurality of components, the plurality of components, the data processing computer, By connecting a test device that individually outputs test information to a plurality of components during the terrestrial test of the satellite, by connecting an interface connector for connecting external devices to the bidirectional bus with each other. It is possible to automate and improve the efficiency of satellite testing and shorten the testing period without having to procure the minimum components necessary for starting the satellite and test equipment for each satellite. There is an effect that the number of people can cope.

[Brief description of the drawings]

FIG. 1 is a block diagram showing a configuration of a satellite test system according to one embodiment of the present invention.

FIG. 2 is a diagram showing an overall configuration of a satellite test system according to one embodiment of the present invention.

FIG. 3 is a diagram showing a peripheral configuration of an artificial satellite according to an embodiment of the present invention.

4A is a diagram illustrating an arrangement example of a bus interface connector in FIG. 1; FIG. 4B is a diagram illustrating an example of connection of a ground test device to the bus interface connector in FIG. 1;

5A is a diagram showing a format of a command word of MIL-STD-1553B, and FIG.
FIG. 3C is a diagram showing a format of a data word of TD-1553B, and FIG. 4C is a diagram showing a format of a status word of MIL-STD-1553B.

6A is a diagram showing a transmission state of the packet definition file shown in FIG. 5, and FIG. 6B is a diagram showing a response transmission state of the packet definition file shown in FIG.

FIG. 7 is a sequence chart showing an example of an artificial satellite test process according to an embodiment of the present invention.

FIG. 8 is a block diagram showing a configuration of a satellite test system according to a conventional example.

FIG. 9 is a diagram showing an entire configuration of a satellite test system according to a conventional example.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Artificial satellite 2 Ground test apparatus 10 Bus interface connector 11 Data processing computer 12-15 Component 16 Satellite antenna 17 RF equipment 100,101 Stub cable

Claims (4)

[Claims] 1. A satellite test system for an artificial satellite equipped with a plurality of components and a data processing computer for controlling the plurality of components, wherein a bidirectional connection between the plurality of components and the data processing computer is provided. A bus, an interface connector for connecting an external device to the bidirectional bus, and a test device connected to the interface connector and for individually outputting test information to the plurality of components during a ground test of the satellite. A satellite test system, characterized in that: 2. The MIL-STD-1 according to claim 1, wherein the bidirectional bus is an MIL-STD-1.
The satellite test system according to claim 1, comprising a stub cable, which is one type of a telemetry / command bus for an artificial satellite specified in 553. 3. The satellite test system according to claim 2, wherein said test device is connected to said interface connector by said stub cable. 4. The test apparatus transmits the test information to the M
4. The satellite test system according to claim 2, wherein the packet is transmitted to each of the plurality of components in a packet definition file defined in IL-STD-1553.