JP2003179608A - Radio communication system among modules and airplane using the same - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a system capable of evading the situation that the entire system becomes inoperable by a fault of a bus due to breakage of a back plane. <P>SOLUTION: A radio communication system 10 among modules in this invention is provided with a plurality of the modules 1 providing functions for communication and flying control and a plurality of radio interfaces 6 to/from which the plurality of the modules 1 respectively output a first data cable signal 1D or input a second data cable signal 2D. The plurality of the radio interfaces 6 are respectively connected with the corresponding modules 1, convert the first data cable signal 1D from the corresponding module 1 to a first data radio signal 1DD and transmit it to the other radio interface 6, and at the time of receiving a second data radio signal 2DD from the other radio interface 6, convert the second data radio signal 2DD to the second data cable signal 2D and output it to the corresponding module 1. <P>COPYRIGHT: (C)2003,JPO

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a backplane wireless system, and more particularly to a system for wirelessly communicating between a plurality of modules connected to the backplane.

[0002]

2. Description of the Related Art A technique relating to a computer device, an interface bus connection mechanism of the computer device, and an expansion board of the computer device is disclosed in Japanese Patent Laid-Open No. 2000-235.
No. 438.

According to this prior art, the connection mechanism of the interface bus of the computer device is the CPU,
Peripheral circuit, an interface circuit with the peripheral device, and a connector for connecting the peripheral device. In addition, the connection mechanism of the interface bus of this computer device,
The number of pins and the shape are the same as those of the socket into which the expansion memory module of the CPU is inserted.

According to this prior art, the expansion board is made of CP.
U, a peripheral circuit of the CPU, an interface circuit with the peripheral device, and a computer device having a connector for connecting the peripheral device. This expansion board is the CP
It has the same number of pins and shape as the socket into which the U expansion memory module is inserted, and has a portion to be inserted into the socket connected to the interface bus of the computer device.

According to this conventional technique, the computer device includes a CPU, a peripheral circuit of the CPU, an interface circuit with the peripheral device, and a connector for connecting the peripheral device. This computer device has an extension board having the same pin number and shape as the socket into which the expansion memory module of the CPU is inserted, and having a portion to be inserted into the socket connected to the interface bus of the computer device. .

A technique relating to a wireless communication device, a communication control method therefor, and a storage medium is disclosed in Japanese Patent Laid-Open No. 2000-2952.
No. 38.

According to this conventional technique, the wireless communication device is mounted on each device so that a plurality of devices including the main device can be connected in series with the main device being the most upstream side. This wireless communication device includes means for generating its own status, downstream receiving means for receiving data transmitted from a device located on the downstream side via a wireless medium, and data received by the downstream receiving means. It is provided with a first logical sum means for inputting the status of itself and performing a logical sum operation. Also, the wireless communication device includes upstream transmission means for transmitting the output of the first logical sum means to a device located on the upstream side via a wireless medium, and wireless communication from the device located on the upstream side via a wireless medium. And upstream receiving means for receiving the transmitted data. Furthermore, a second logical sum means for inputting the output of the first logical sum means and the data received on the upstream side to perform a logical sum operation, and an output of the second logical sum means for the wireless medium. Downstream side transmitting means for transmitting to the device located on the downstream side via the above.

According to this prior art, the communication control method of the wireless communication device is provided with the presence / absence of its own status and the presence / absence of reception of data transmitted from the device located on the downstream side by the downstream side receiving means via the wireless medium. And a step of monitoring the presence or absence of reception of the data transmitted via the wireless medium from the device located on the upstream side by the upstream side reception means. In addition, the communication control method of the wireless communication device includes transmitting the status of itself based on the monitoring result, transmitting the data received by the downstream receiving unit by the upstream transmitting unit to the upstream unit, and transmitting the downstream side. There is a step of controlling the means to transmit the data received by the upstream side reception means to the downstream side device according to a preset priority order.

According to this conventional technique, the storage medium has a communication control of a wireless communication device mounted on each device so that a plurality of devices including the main device can be connected in series with the main device being the most upstream side. Contains the program. The communication control program is located on the upstream side by the upstream receiving means, by the presence / absence of occurrence of its own status, by the downstream receiving means on the presence / absence of data transmitted from the device located on the downstream side via the wireless medium. It has a module for monitoring whether or not the data transmitted from the device via the wireless medium is received. In addition, the communication control program, based on the monitoring result, the upstream side transmission means transmits the status of itself, the upstream side transmission means transmits the data received by the downstream side reception means to the upstream side device,
It has a module for controlling the downstream side transmitting means to transmit the data received by the upstream side receiving means to the downstream side device in accordance with a preset priority order.

Here, a system conventionally used in electronic equipment (avionics) constituting an aerial vehicle (aircraft, etc.) will be described with reference to FIG.

The system shown in FIG. 8 has an LRM1 (1a,
1b, 1c, 1d), a backplane (general name of a board that functions as a bus) 2, and a system bus 3 represented by a VME bus. LRM (Line
The Replaceable Module 1 provides functions for communication and flight control, and the basic configuration is the same as that of the module. Further, the wiring of the system bus 3 is provided on the backplane 2 (the number is one in the example of FIG. 8, but it may be plural). Furthermore, the LRM 1 and the external device 8 controlled by the LRM 1 are connected by signal lines 7 (3 in the example of FIG. 8).

The LRM 1 has a first terminal 4 (4a, 4b, 4
c, 4d) and the system bus 3 has a second terminal 5
(5a, 5b, 5c, 5d). The LRM 1 and the system bus 3 are connected by connecting the first terminal 4 and the second terminal 5.

In the configuration shown in FIG. 8, the number of LRM1 is four. Here, in FIG. 8, for example, LRM1a and LRM
1b has the same function (for example, LRM1d of the same data)
To the LRM1a), and normally the LRM 1a is performing the function. In this case, LRM1
Even when a failure occurs in a, it is possible to continue the operation of the entire system by the LRM 1b executing its function. However, the number of backplanes 2 is one. Therefore, when the backplane 2 is damaged (in an aircraft, the damage may occur due to an impact at the time of takeoff and landing, etc.), the effect of the damage is the system bus 3
Moreover, the operation of the entire system may be disabled as a result.

[0014]

SUMMARY OF THE INVENTION It is an object of the present invention to provide a system capable of avoiding a situation where the entire system becomes inoperable due to a bus failure caused by damage to a backplane.

[0015]

[Means for Solving the Problems] Means for solving the problems will be described below with reference to the numbers and symbols used in the embodiments of the present invention. These numbers and signs are added to clarify the correspondence between the description in [Claims] and the description in [Embodiment of the Invention], but in [Claims] It should not be used to interpret the technical scope of the described invention.

A wireless communication system (10) between modules according to the present invention includes a plurality of modules (1) providing functions for communication and flight control, and each of the plurality of modules (1) includes first data. A wired signal (1D) is output or a second data wired signal (2D) is input, and a plurality of wireless interfaces (6) are provided. Each of the plurality of wireless interfaces (6) is connected to a corresponding module (1) and converts the first data wired signal (1D) from the corresponding module (1) into a first data wireless signal (1DD). And transmits to the other wireless interface (6) and receives the second data wireless signal (2DD) from the other wireless interface (6), the second data wireless signal (2DD) is transmitted to the second data wired line. A signal (2D) is converted and output to the corresponding module (1).

In the wireless communication system (10) between modules according to the present invention, the wireless interface (6) and the other wireless interface (6) send the first data wireless signal (1DD) to the other wireless interface ( 6) and a transmitting / receiving unit (6aa) for transmitting the other second data wireless signal (2DD) from the other wireless interface (6), and the second data wireless signal (2DD) for the second data. A first conversion unit (6ab) for converting a wired signal (2D) and a second conversion unit (6ac) for converting the first data wired signal (1D) into the first data wireless signal (1DD). ing.

In the wireless communication system (10) between modules according to the present invention, the wireless interface (6) and the other wireless interface (6) send the first data wireless signal (1DD) to the other wireless interface ( 6) a transmitting unit (6aa-1) for transmitting to
A receiving unit (6aa-2) for receiving the second data wireless signal (2DD) from the other wireless interface (6).
It is equipped with. The wireless interface (6) and the other wireless interface (6) include a first converter (6ab) that converts the second data wireless signal (2DD) into the second data wired signal (2D). It further comprises a second converter (6ac) for converting the first data wired signal (1D) into the first data wireless signal (1DD).

In the wireless communication system (10) between modules according to the present invention, a module (9) having a wireless communication function including the module (1) and the wireless interface (6) or the other wireless interface (6) is provided. At least one of a gap between an outer wall (14) of the aircraft body (11) and a cabin inner wall (15) of the aircraft body (11), and a gap inside the wing (11-1) of the aircraft body (11). Is installed in.

In the wireless communication system (10) between the modules according to the present invention, the mutual arrangement interval of the plurality of modules (9) with wireless communication function and the arrangement shape of the plurality of modules (9) with wireless communication function are as follows. It is optional.

In the wireless communication system (10) between modules according to the present invention, the first data wireless signal (1
DD) and the second data wireless signal (2DD) are radio signals, and the outer wall (14) of the aircraft body (11),
A seal is provided on an inner wall (15) of the cabin of the aircraft body (11) and a wing (11-1) of the aircraft body (11) to prevent transmission of the radio signal.

In the wireless communication system (10) between modules according to the present invention, the first data wireless signal (1
DD) and the second data wireless signal (2DD) are ultrasonic signals.

In the wireless communication system (10) between modules according to the present invention, the first data wireless signal (1
DD) and the second data wireless signal (2DD) are infrared signals.

In the wireless communication system (10) between modules according to the present invention, the first data wireless signal (1
DD) and the second data wireless signal (2DD) are visible light signals.

In the wireless communication system (10) between modules according to the present invention, the first data wireless signal (1
DD) and the second data wireless signal (2DD) are laser beam signals.

The inter-module wireless communication system (10) according to any one of claims 1 to 10 is used in an aircraft (11).

[0027]

BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of a wireless communication system 10 between modules according to the present invention will be described below with reference to the accompanying drawings.

FIG. 1 is a block diagram according to an embodiment of a wireless communication system 10 between modules of the present invention. The wireless communication system 10 between the modules is LRM1.
(1a, 1b, 1c, 1d), wireless interface 6
(6-1, 6-2, 6-3, 6-4). The wireless interface 6 is connected to each LRM 1.

FIG. 2 is a block diagram showing an example of the LRM 1. The LRM 1 has a CPU 1aa, an external device interface 1bb, a memory 1cc, and a bus interface 1dd. The LRM1 is mainly used in an aircraft, and its basic configuration is the same as that of a module (or a board). Therefore, all "LRM1" in the following description can be replaced with "module 1 (or substrate 1)". "Module 1"
May be referred to as a "VME module" by taking the name of the bus to which it is particularly connected.

The LRM 1 outputs the first data wired signal 1D to the wireless interface 6 or inputs the second data wired signal 2D from the wireless interface 6. The LRM 1 also performs processing in response to the second data wired signal 2D output from the wireless interface 6. First
The data wired signal 1D and the second data wired signal 2D are necessary signals for holding the external attitude of the aircraft 8 when the external equipment 8 holds the flight attitude of the aircraft. The external device 8 is controlled based on this signal.

Any of LRM1 (for example, LRM
1a) controls another LRM1 (for example, LRM1b). In this case, the LRM 1a outputs, to the LRM 1b, a first data wired signal 1D indicating a control method (for example, a flight attitude control method) of the external device 8b to the wireless interface 6. The first data wired signal 1D is converted into the first data wireless signal 1DD by the wireless interface 6 and then transmitted to another wireless interface 6.
Further, the first data wireless signal 1DD is converted into the second data wired signal 2D by another wireless interface 6 and then output to the LRM 1b. The LRM 1b controls the external device 8b based on the second data wired signal 2D.
The wireless interface 6 and the other wireless interface 6 may be any of the wireless interfaces 6-1 to 4-1.

The LRM1 is provided with measures (a redundancy of the LRM1) assuming the failure. in this case,
Consider a system as shown in FIG.

In FIG. 3, the LRM 1d transmits the first data radio signal 1DD via the radio interface 6-4. The wireless interface 6-1, the wireless interface 6-2, and the wireless interface 6-3 receive the first data wireless signal 1DD and receive the second data wired signal 1D.
LRM1a, LRM1b, L respectively
Output to RM1c. Furthermore, LRM1a, LRM1b,
And the LRM 1c outputs a control signal based on the second data wired signal 1D to the external device 8 via the signal line 7.

Here, it is assumed that there is no failure in any of the signal lines 7. In this case, the external device 8 is shown in FIG.
Based on LRM1a, LRM1b, and LRM1c
It is determined whether the signal output from is true or false and whether there is a failure in LRM1.

In FIG. 4, the signal output from the LRM 1a is 5A (either the first signal LL or the second signal HH, 5B and 5C are the same), and the signal output from the LRM 1b is 5B, the output from the LRM 1c. It indicates that the signal to be processed is 5C. Further, of the signals received by the external device 8, the true signals 5D and LR representing the signals determined to be true.
M status (indicates LRM that external device 8 has determined to be defective) 5
Represents E.

For example, when the first case 1N is N1 (or N8), LRM1a, LRM1b, and LRM1
No failure has occurred in c, so the external device 8 determines that the true signal 4D is the first signal LL (or the second signal H).
H). Further, when the first case N is N2 (or N7), the LRM 1c has a failure. Therefore, in this case, the external device 8 determines that the true signal 4D is the first signal LL (or the second signal HH) and performs necessary processing. Hereinafter, the series of processes performed by the external device 8 described with reference to FIG. 4 will be referred to as “majority decision process”.

In some cases, a BIT (Built in test) function may be provided instead of the majority voting process described with reference to FIG. The BIT function is a function for diagnosing a failure of the installed LRM 1, and this function disconnects the LRM 1 determined to be a failure from the system.

FIG. 5 shows the configuration (general) of the LRM 9 with a wireless communication function. The wireless interface 6 included in the LRM 9 with wireless communication function includes an antenna 6aa, a first converter 6ab, and a second converter 6ac.

The antenna 6aa transmits the first data radio signal 1DD output from the first converter 6ab. Alternatively, the received second data wireless signal 2DD is output to the second conversion unit 6ac. In FIG. 5, the antenna 6aa is used for both transmission and reception, but the configuration is not limited to this, and it is also possible to separately install the transmission antenna 6aa-1 and the reception antenna 6aa-2. In this case, the transmitting antenna 6a
a-1 is connected to the first conversion unit 6ab, and the first conversion unit 6a
The first data wireless signal 1DD output from b is transmitted. In addition, the receiving antenna 6aa-2 is the second conversion unit 6a.
The second data wireless signal 2DD which is connected to the second data wireless signal c is output to the second conversion unit 6ac.

The first converter 6ab converts the first data wired signal 1D received from the LRM 1 into a first data wireless signal 1DD that can be transmitted from the antenna 6aa (or the transmitter 6aa-1). Further, the first conversion unit 6ab is
The data wireless signal 1DD is modulated and output to the antenna 6aa (or the transmission unit 6aa-1). 2nd conversion part 6ac
Demodulates the second data wireless signal 2DD output from the antenna 6aa (or the receiving unit 6aa-2) into the second data wired signal 2D, and further the second data wired signal 2D
Output D to LRM1.

In FIG. 6, the LRM 1 to which the wireless interface 6 is connected (hereinafter, referred to as LRM 9 with wireless communication function).
The arrangement example (12, 13) is shown. In FIG. 6, the arrangement example 12
Is the aircraft outer wall 14 (shown in cross section in FIG. 6) and the cabin (or cockpit) inner wall 15 (shown in cross section in FIG. 6)
LRM9 (9-1, 9 with wireless communication function in the gap between
-2, 9-3, 9-4).
Arrangement example 13 shows an arrangement example of the LRM 9 with a wireless communication function in a gap inside the wing 11-1 of the aircraft body 11. The LRM 9 with the wireless communication function is arranged according to at least one of the arrangement example 12 and the arrangement example 13. However, the arrangement example is not limited to the above example, and may be an arbitrary place inside the aircraft body 11.

The arrangement intervals and arrangement shapes (on a straight line, circles, etc.) of the individual LRMs 9 with wireless communication functions are arbitrary, and they can be arranged in consideration of the installation space inside the aircraft main body 11 and the like. Furthermore, for example, if an amplifier is installed at an appropriate location, it is possible to dispose the LRM 9 with a wireless communication function via a wall such as a partition wall.

For communication between the wireless interfaces 6,
It is possible to use a part of the wireless LAN technology. As specifications used for the wireless LAN, there are Bluetooth, IEEE 802.11 and the like (the configuration is shown in FIG. 5). IEEE 802.11 is a specification standardized by an IEEE subcommittee on standardization of wireless LANs.
4 GHz band radio waves and infrared rays are used for the transmission method. Bluetooth incorporates a wireless circuit into a personal digital assistant,
It is a standard for wirelessly connecting to personal computers and peripheral devices.

The wireless LAN is normally used for communication within a range of several meters to several hundred meters, but in the present invention, it is within a narrower range (within a range connectable by wire). The wireless LAN technology is also used for the communication. Specifically, in a place where a wired LAN is not installed (places shown in Arrangement Example 12 and Arrangement Example 13), the LRMs 9 with a wireless communication function communicate with each other by a radio wave signal. When performing this communication, the inner peripheral portion 14-1 of the outer wall 14 of the aircraft body and the outer peripheral portion 1 of the passenger compartment inner wall 15
5-1 and the inner peripheral portion 16-1 of the blade 16 are provided with a seal for preventing transmission of radio signals.

Instead of the radio wave signal or the infrared ray signal used in the wireless LAN, it is possible to perform communication between the LRMs 9 with a wireless communication function by using any one of an ultrasonic wave signal, a visible ray signal and a laser ray signal. Is.

The signal line 7 connects the LRM 1 and the external device 8, and is provided with a plurality of lines (three lines in the example of FIG. 1) as shown in FIGS. When all of the plurality of signal lines 7 are normal, the plurality of signal lines 7
A signal based on the second data wired signal 2D is transmitted from the LRM 1 to the external device 8 via the specific signal line 7 among them. When a failure occurs in a specific signal line 7 (disconnection of the signal line 7, etc.), a signal is transmitted from the LRM 1 to the external device 8 via the other signal line 7 of the plurality of signal lines 7. It

The external device 8 receives a signal through a specific signal line 7 of the plurality of signal lines 7 (three in the example of FIGS. 1 and 8) and performs processing based on the control signal. . Alternatively, the external device 8 receives a signal via the other signal line 7 of the plurality of signal lines 7 and performs processing based on the signal.

Next, the processing according to the embodiment of the backplane radio system 10 of the present invention will be described with reference to FIG. The following description will be given based on FIG. Further, the following description is an example in the case where the signal output from the LRM 1a via the wireless interface 6a in FIG. 2 is input to the LRM 1d via the wireless interface 6d. However, the output destination and the input destination of the signal are different from each other.
It may be RM1.

The LRM 1a is the first data wire signal 1D.
Is output to the first conversion unit 6ab of the wireless interface 6-1 (step S1). The first conversion unit 6ab has a first
The data wired signal 1D is converted into the first data wireless signal 1DD and output to the antenna 6aa (step S2). The antenna 6aa transmits the first data wireless signal 1DD to the antenna 6aa of the wireless interface 6-4 (step S3). Antenna 6 of wireless interface 6-4
The aa receives the second data wireless signal 1DD (here, equal to the first data wireless signal 1DD) (step S).
4). The second conversion unit 6ac uses the second data wireless signal 2DD.
To a second data wired signal 2D (here, the same as the first data wired signal 1D) and output to the LRM 1d (step S5). The LRM 1d transmits a signal based on the second data wired signal 2D to the external device 8d via the specific signal line 7 (step S6). The external device 8d is
Processing based on the signal is performed (step S7).

[0050]

According to the wireless communication system between modules of the present invention, it is possible to avoid a situation where the entire system becomes inoperable due to the damage of the backplane.

[Brief description of drawings]

FIG. 1 is a diagram showing a configuration related to a wireless communication system between modules of the present invention.

FIG. 2 is a diagram showing a general configuration of an LRM according to a wireless communication system between modules of the present invention.

FIG. 3 is a diagram showing an example of a system in which redundancy of LRM is applied in a wireless communication system between modules of the present invention.

FIG. 4 is a diagram used for explaining a method of determining a true control signal in an external device according to a wireless communication system between modules of the present invention.

FIG. 5 is a diagram showing a general configuration of an LRM with a wireless communication function according to a wireless communication system between modules of the present invention.

FIG. 6 is a diagram showing an arrangement example of an LRM with a wireless communication function in an aircraft body according to a wireless communication system between modules of the present invention.

FIG. 7 is a diagram showing processing performed by the wireless communication system between modules of the present invention.

FIG. 8 is a diagram showing a configuration of a conventional technique related to a wireless communication system between modules of the present invention.

[Explanation of symbols]

1 (1a, 1b, 1c, 1d) LRM 1aa CPU 1bb External device interface 1cc Memory 1dd Bus interface 2 Backplane 3 System bus 4 (4a, 4b, 4c, 4d) First terminal 5 (5a, 5b, 5c, 5d) ) Second terminal 6 (6-1, 6-2, 6-3, 6-4) Radio interface 6aa Antenna 6aa-1 Transmission antenna 6aa-2 Reception antenna 6ab First converter 6ac Second converter 7 Signal Line 8 (8a, 8b, 8c, 8d) External device 9 LRM with wireless communication function 4A, 4B, 4C Signal 4D True signal 4E LRM situation 11 Aircraft body 12, 13 Arrangement example of LRM9 with wireless communication function 14 Aircraft outer wall portion 15 Interior wall of guest room

Claims (11)

[Claims] 1. A plurality of modules providing functions for communication and flight control, and each of the plurality of modules outputs a first data wired signal or inputs a second data wired signal, A wireless interface, each of the plurality of wireless interfaces is connected to a corresponding module, and the first data wired signal from the corresponding module is converted into a first data wireless signal and transmitted to another wireless interface. A wireless communication system between modules that, when receiving a second data wireless signal from the other wireless interface, converts the second data wireless signal into the second data wired signal and outputs the second data wired signal to the corresponding module. 2. The transmission / reception in which the wireless interface and the other wireless interface transmit the first data wireless signal to the other wireless interface and receive the other second data wireless signal from the other wireless interface. A first conversion unit that converts the second data wireless signal into the second data wired signal; and a second conversion unit that converts the first data wired signal into the first data wireless signal. A wireless communication system between the modules according to Item 1. 3. The wireless interface and the other wireless interface, a transmitter for transmitting the first data wireless signal to the other wireless interface, and receiving the second data wireless signal from the other wireless interface. A receiving unit, a first converting unit that converts the second data wireless signal into the second data wired signal, and a second converting unit that converts the first data wired signal into the first data wireless signal. A wireless communication system between modules according to claim 1. 4. A module with a wireless communication function, including the module and the wireless interface or the other wireless interface, wherein a gap between an outer wall of an aircraft body and an inner wall of a cabin of the aircraft body, and an inside of a wing of the aircraft body. The wireless communication system between modules according to any one of claims 1 to 3, wherein the wireless communication system is installed in at least one of the gaps. 5. The module according to any one of claims 1 to 4, wherein an arrangement interval between the plurality of modules with wireless communication functions and an arrangement shape of the plurality of modules with wireless communication functions are arbitrary. Wireless communication system. 6. The first data wireless signal and the second data wireless signal are radio wave signals, and are the inner peripheral portion of the outer wall of the aircraft body, the outer peripheral portion of the inner wall of the cabin of the aircraft body, and the wing of the aircraft body. The wireless communication system between modules according to any one of claims 1 to 5, wherein a seal is provided on a peripheral portion to prevent transmission of the radio wave signal. 7. The wireless communication system between modules according to claim 1, wherein the first data wireless signal and the second data wireless signal are ultrasonic signals. 8. The wireless communication system between modules according to claim 1, wherein the first data wireless signal and the second data wireless signal are infrared signals. 9. The wireless communication system between modules according to claim 1, wherein the first data wireless signal and the second data wireless signal are visible light signals. 10. The first data radio signal and the second data radio signal
The wireless communication system between modules according to any one of claims 1 to 5, wherein the data wireless signal is a laser beam signal. 11. An aircraft using the inter-module wireless communication system according to claim 1. Description: