JP6789192B2 - Aircraft data bus line connection method - Google Patents

Description

The present invention relates to an existing aircraft data bus line having a predetermined data transmission format and a connection structure for connecting a new electronic device or sensor.

In aircraft, multiple electronic devices and sensors are operated via data bus lines. The data transmission format on the data bus line is common. That is, in an aircraft equipped with a data bus line of a predetermined data transmission format, the equipment used connected to the data bus line is based on the data transmitted in the data bus line of the predetermined data transmission format. Works.

On the other hand, many types of aircraft are in operation, but the data transmission format on the data bus line is different for each aircraft. Therefore, a device that operates using a data bus line of one data transmission format cannot operate using data from a device of another data transmission format. That is, when connecting a new electronic device or sensor to an existing aircraft data bus line, some ingenuity is required.

It should be noted that a prior art has been proposed in which data is converted between two existing data bus lines of different data transmission formats (ARINC429 and ARINC629) so that they can be used mutually (for example, Patent Document 1).

However, the technique according to Patent Document 1 cannot correspond to a newly installed electronic device or sensor.

Japanese Unexamined Patent Publication No. 10-109697

In order to operate an existing aircraft data bus line that has a predetermined data transmission format by using the data of a new electronic device or sensor with a different data transmission format, the following methods can be roughly divided. Be done.
-Repair new electronic devices or sensors themselves to make the data transmission format compatible with the existing data bus line of the aircraft.
-Add a new data bus line that fits the new electronics or sensors.
-Modify the control device connected to the existing data bus line to enable different data transmission formats.

However, the data bus line used in the aircraft may be different from the general data bus line. The number used is overwhelmingly smaller than that of general-purpose data bus lines. In addition, the data transmission format is often customized for each aircraft model.

Therefore, it is necessary to take specific measures individually, and it takes a lot of cost and time to develop a new dedicated device, and there is a problem that a longer period of test and repair is required to mount it on the airframe.

The present invention solves the above problems, and at a much lower cost and time than before, a new electronic device or sensor having a different data transmission format is used for an existing aircraft data bus line having a predetermined data transmission format. The purpose is to provide a technology for connecting data by making it adaptable.

The present invention solves the above problems in an existing electronic device or sensor mounted on an aircraft, an aircraft data bus line that transmits a signal from the existing electronic device or sensor in a predetermined data transmission format, and an aircraft. The newly installed electronic device or sensor that is mounted and transmits data in a data transmission format different from the predetermined data transmission format is interposed between the aircraft data bus line and the new electronic device or sensor. An aircraft data bus line articulated structure comprising a built-in controller that stores a program that newly generates data in a data transmission format compatible with the aircraft data bus line based on a signal from the electronic device or sensor of the above. ..

In the above invention, preferably, the embedded controller inputs a plurality of data from the newly installed electronic device or sensor, generates one data, and outputs the data to the aircraft data bus line.

In the above invention, preferably, the embedded controller has environmental resistance and electromagnetic compatibility.

The present invention, which solves the above problems, comprises an aircraft equipped with an existing electronic device or sensor and an aircraft data bus line that transmits a signal from the existing electronic device or sensor in a predetermined data transmission format. Conforms to the aircraft data bus line based on the process of mounting a new electronic device or sensor that transmits data in a data transmission format different from the predetermined data transmission format and the signal from the new electronic device or sensor. A step of storing a program for newly generating data in a possible data transmission format in an embedded controller, a step of interposing the embedded controller between the aircraft data bus line and the newly installed electronic device or sensor, and a step of interposing the embedded controller between the aircraft data bus line and the newly installed electronic device or sensor. An aircraft data bus including a step of causing the embedded controller to newly generate and output data in a data transmission format compatible with the aircraft data bus line based on a signal from the newly installed electronic device or sensor. This is a line connection method.

The present invention, which solves the above problems, comprises an aircraft equipped with an existing electronic device or sensor and an aircraft data bus line that transmits a signal from the existing electronic device or sensor in a predetermined data transmission format. A process of mounting a new electronic device or sensor that transmits data in a data transmission format different from the predetermined data transmission format, and an embedded controller between the aircraft data bus line and the new electronic device or sensor. The step of interposing, the step of storing in the embedded controller a program for newly generating data in a data transmission format compatible with the aircraft data bus line based on the signal from the newly installed electronic device or sensor. An aircraft data bus including a step of causing the embedded controller to newly generate and output data in a data transmission format compatible with the aircraft data bus line based on a signal from the newly installed electronic device or sensor. This is a line connection method.

In the above invention, preferably, a step of detachably connecting a general-purpose computer equipped with a normal operation confirmation program for confirming whether or not the program performs a desired function to the embedded controller, and the normal operation confirmation program. The general purpose computer is further provided with a step of ascertaining whether or not the program performs a desired function.

In the above invention, preferably, a step of detachably connecting a function expansion medium containing a function expansion program that enables the newly generated data to be used by an existing electronic device or sensor to the embedded controller. The function expansion program is further provided with a step of extending the function of the existing electronic device or sensor so that the newly generated data can be used.

In the above invention, preferably, a step of detachably connecting a function expansion medium containing a function expansion program that enables the newly generated data to be used by an existing monitor or recording device to the embedded controller. The function extension program is used to extend the function so that the existing monitor can display the newly generated data, or the recording device can record the newly generated data. It also has a process to do.

In the above invention, preferably, the aircraft data bus line of the predetermined data transmission format is MIL-1553 or ARINC standard.

According to the aircraft data bus line articulated structure according to the present invention, a new electronic device having a different data transmission format or a new electronic device having a different data transmission format than an existing aircraft data bus line having a predetermined data transmission format at a much lower cost and time than before. The data from the sensor can be made adaptable.

Schematic configuration diagram of the aircraft data bus line articulated structure according to this embodiment An example of data transmission format for aircraft data bus lines An example of new data generation processing An example of new data generation processing An example of new data generation processing Another example of new data generation processing Functional block diagram of the embedded controller Conceptual diagram of the state in which the function expansion medium is detachably connected

~Overview~
FIG. 1 is a schematic configuration diagram of an aircraft data bus line articulated structure according to the present embodiment.

The aircraft is conventionally equipped with an aircraft data bus line 10 and a navigation system 12 in a predetermined data transmission format. The aircraft data bus line 10 of this embodiment is, for example, MIL-1553 or ARINC (American Radio Inc.) standard.

Further, the aircraft is equipped with existing electronic devices (for example, an inertial navigation system 18) and is connected to the aircraft data bus line 10. The data transmission format of the inertial navigation system 18 is the same as the data transmission format of the aircraft data bus line 10.

By the way, in the conventional aircraft, the position information data from the terrestrial radio navigation system is based on the INS (Inertial Navigation System) position information data sent from the inertial navigation system 18 to the navigation system 12 via the aircraft data bus line 10. The position information during the flight was obtained by correcting with. However, when the position information data from the terrestrial radio navigation system is abolished, the error becomes larger as the distance from the departure point of the aircraft increases only with the position information during flight based on the INS position information data.

In this embodiment, GPS (Global) is a kind of electronic device having a different data transmission format.
The Positioning System) device 16 is newly installed and is retrofitted to the aircraft data bus line 10 of the navigation system 12 via the embedded controller 14. In other words, the embedded controller 14 is interposed between the aircraft data bus line 10 and the newly installed GPS device 16.

If the GPS position data from the new GPS device 16 becomes available to the navigation system 12, the GPS position data can be used in combination with the INS position information data from the existing inertial navigation system 18 during flight of the aircraft. The error of the position information can be made smaller.

The embedded controller 14 inputs GPS position data from the GPS device 16 having a data transmission format different from the data transmission format of the aircraft data bus line 10, and after performing a predetermined calculation, it is converted to the data transmission format of the aircraft data bus line 10. After newly generating compatible data, it is sent to the navigation system 12.

The navigation system 12 can use GPS position data. The navigation system 12 obtains the position information during flight of the aircraft by using the GPS position data while the GPS position data can be acquired, corrects the error of the INS position data, and INS while the GPS position data cannot be acquired. Only position data is used to obtain in-flight position information of the aircraft, and when GPS position data acquisition is resumed, GPS position data is used to obtain in-flight position information of the aircraft and INS position data errors. To fix.

~ Data generation ~
FIG. 2 is an example of a data transmission format of an aircraft data bus line. It shows ARINC 429. The upper part of the figure shows the basic form of ARINC 429. Of the 32 bits, 1 to 8 bits indicate a 3-digit label. 11 to 28 bits are used as the data area. Other bits store other information.

The lower part of the figure is an example of customization of ARINC 429. 1 to 8 bits indicate label label 310 (latitude information). Expand the data area to 9 to 28 bits and use it. In this way, even the ARINC 429 is customized for each aircraft, and in order to make the data from newly installed electronic devices compatible with the aircraft data bus line, it is necessary to take individual and specific measures.

3 to 5 are examples of new data generation processing. In the present embodiment, the embedded controller 14 newly generates data in a data transmission format compatible with the aircraft data bus line 10 based on the signal from the newly installed GPS device 16.

The data from the GPS device 16 has ARINC 429 Label information. The label is a unique octadecimal notation for the parameter, and has a parameter (Parameter), a format (Format), and a rate (Rate) for each Label 310,311,261,275.

The parameter of label 310 is latitude
It is (Latitude), the format is 429BNR (Binary Numbers), and the rate is 200ms. The parameter on label 311 is Longitude and the format is 429BNR (Binary).
Numbers), and the rate is 200ms. The parameter on label 261 is GPS DISCRETE WPRLD, the format is 429DISC (Discrete), and the rate is 1000ms. The parameter on label 275 has a Status of GAMA (General Aviation).
Manufactures Association), the format is 429 DISC (Discrete), and the rate is 200ms.

As described above, even the ARINC 429 is customized, and even if the data from the GPS device 16 having a different data transmission format is sent to the aircraft data bus line 10, it cannot be used by other devices (for example, the navigation system 12).

The embedded controller 14 inputs data from the GPS device 16, performs a predetermined calculation, newly generates data compatible with the data transmission format of the aircraft data bus line 10, and then sends the data to the navigation system 12. This will be described in detail below.

The rate of the data related to Labels 310 and 311 has been converted to 400 ms.

The data related to Labels 261, 275 is newly generated as the data related to Label 371. The status of the parameter on Label 371 is LORAN (long-range navigation). It is a parameter used in the terrestrial radio navigation system, and can be used by the navigation system 12 in the same manner as the INS position data. The format is DISC
It remains (Discrete). The rate is unified to 400ms.

That is, the embedded controller 14 inputs a plurality of data from the newly installed GPS device 16, generates one new data, and outputs the new data to the aircraft data bus line. A program related to the data generation is stored in the embedded controller 14, and the calculation unit 14A executes the program. The following will be described in more detail.

In the data related to Label 261, 24-bit indicates whether or not the positioning information is reliable. In the data related to Label 275, 12 bits indicate whether or not the positioning information is reliable. In the data related to Label 275, 22 bits indicate the presence or absence of self-contained navigation.

The embedded controller 14 has 24 bits of the data related to the label (Label) 261 being 1, 12 bits of the data related to the label (Label) 275 being 1, or 22 of the data related to the label (Label) 275. If the state in which the bit is 1 continues for t seconds or more, or in any case, data relating to the label (Label) 371 is newly generated, and 27 bits are set to 1. The 27 bits of the data according to Label 371 indicate signal integrity.

~ Another example of data generation ~
In the present embodiment, the GPS device 16 has been described as an example of a newly installed electronic device or sensor, but the present invention is not limited to the GPS device 16. As a new electronic device or sensor, a flight specification measuring device such as a load frequency measuring device or a strain measuring device, an external observation camera, or the like can be considered.

FIG. 6 is another example of the new data generation process.

In the data related to the signal A, 24 bits indicate the signal state α. In the data related to signal B, 17 bits indicate the equipment state β. In the data related to signal B, 22 bits indicate the signal state γ.

The embedded controller 14 generates new data when the signal state α, the equipment state β, or the signal state γ continues for 3 seconds or more, and the equipment / signal is sound. The 27 bits indicating the property are set to 1, and output as signal C.

~motion~
FIG. 7 is a functional block diagram of the embedded controller. A specific operation of the embedded controller 14 will be described with reference to the functional block diagram.

The embedded controller 14 stores the GPS position information from the GPS device 16 in the data buffer 14a.

The navigation system 12 outputs a request signal to the embedded controller 14 via the aircraft data bus line 10 as needed.

In response to a request from the navigation system 12, the embedded controller 14 generates new data based on the GPS position information stored in the data buffer 14a and outputs it to the aircraft data bus line 10. The new data is the same as the data transmission format of the existing aircraft data bus line and can be adapted by the navigation system 12.

The navigation system 12 uses the new data together with the INS position information from the inertial navigation system 18.

~ Built-in controller ~
In this embodiment, an embedded controller (Embedded Rugged Computer) is used. As an example, AB3000 Embedded Rugged manufactured by Ballard Technology, USA
There are computers and so on.

Such an embedded controller has been conventionally used for individual control of each device of an aircraft. Compared to a general-purpose controller, the processing content is limited, so the configuration is simple and it is commercially available at a low price. It is easy to obtain.

Also, for mounting on aircraft, environmental resistance: MIL-STD-810, electromagnetic compatibility (EMC): MIL-STD-461, aircraft mountable standard: DO-160, aircraft power supply standard: MIL-STD- Tests such as 704 have been made in advance.

The above programs can be easily stored using open source software and software development kits.

By using such an embedded controller, even if the data transmission format is customized in the existing aircraft, it is possible to individually and concretely deal with it.

By the way, in any case, when repairing a new electronic device or sensor itself, adding a new data bus line, or repairing an existing control device, a confirmation test is performed to see if it can be mounted on an aircraft. There is a need.

On the other hand, since the embedded controller has undergone a confirmation test before purchase, the confirmation test can be omitted, and in this respect as well, cost and time can be greatly reduced.

~Method~
First, in an existing aircraft, a signal from an existing electronic device or sensor (for example, an inertial navigation system 18) uses data in a predetermined data transmission format via an aircraft data bus line 10. It is transmitted to (for example, the navigation system 12). Further, a new electronic device or sensor (for example, GPS device 16) that transmits data having a different data transmission format is installed.

Next, the program related to new data generation is stored in the embedded controller 14, and the embedded controller 14 is interposed between the aircraft data bus line 10 and a newly installed electronic device or sensor (for example, GPS device 16).

Even if the embedded controller 14 is interposed between the aircraft data bus line 10 and a newly installed electronic device or sensor (for example, GPS device 16) and the program related to new data generation is stored in the embedded controller 14. Good.

The embedded controller 14 newly generates and outputs data in a data transmission format compatible with the aircraft data bus line 10 based on a signal from a newly installed electronic device or sensor (for example, GPS device 16). Existing electronic devices that use the data (for example, the navigation system 12) can also use newly generated data.

Further, when adding another new electronic device or sensor, the program stored in the embedded controller 14 may be rewritten, or another embedded controller 15 may be added.

~Scalability~
FIG. 8 is a conceptual diagram of a state in which the function expansion medium is detachably connected.

The embedded controller 14 stores a function expansion medium 20 that stores various function expansion programs capable of expanding the functions of a device or the like (for example, a navigation system 12) that uses newly generated data via the aircraft data bus line 10. Can be detachably connected.

In addition, as a device that uses newly generated data, a monitor, a recording device, or the like can be considered.

Further, the embedded controller 14 is equipped with a normal operation confirmation program in order to confirm whether the stored program, the rewritten program, and various function extension programs can normally operate the desired functions. The general-purpose computer 22 can be detachably connected to the embedded controller 14 via the computer I / F medium 24.

The function expansion medium 20 can be attached / detached to / from the embedded controller 14 or the general-purpose computer 22 can be attached / detached to / from the embedded controller 14. It can be done before or after being intervened.

10 ... Aircraft data bus line, 12 ... Navigation system, 14 ... Embedded controller, 14A ... Calculation unit, 14 a ... Data buffer, 15 ... Embedded controller (additional), 16 ... GPS device, 18 ... inertial navigation system, 20 ... function expansion medium, 22 ... general-purpose computer, 24 ... computer I / F medium

Claims (8)

With existing electronic devices or sensors on board the aircraft,
An aircraft data bus line that transmits signals from the existing electronic devices or sensors in a predetermined data transmission format, and
A new electronic device or sensor that is mounted on an aircraft and transmits data in a data transmission format different from the predetermined data transmission format.
Intervening between the aircraft data bus line and the new electronic device or sensor, a plurality of signals are input from the new electronic device or sensor, and a new data label and parameters of the existing electronic device or sensor are displayed. wherein the data of the data transmission format adaptable to the aircraft data bus lines and generates a new, unidirectionally, aircraft data bus lines connecting structure characterized by comprising a built-in controller that stores an output program .. The aircraft data bus line articulated structure according to claim 1 , wherein the embedded controller has environmental resistance and electromagnetic compatibility. An aircraft equipped with an existing electronic device or sensor and an aircraft data bus line that transmits a signal from the existing electronic device or sensor in a predetermined data transmission format is different from the predetermined data transmission format. The process of installing a new electronic device or sensor that transmits data in the data transmission format, and
Multiple signals are input from the new electronic device or sensor to generate new data in a data transmission format compatible with the aircraft data bus line, including a new data label and parameters of the existing electronic device or sensor. Then, in one direction, the process of storing the output program in the embedded controller,
The process of interposing the embedded controller between the aircraft data bus line and the newly installed electronic device or sensor, and
A data transmission format that inputs a plurality of signals from the new electronic device or sensor to the embedded controller, includes a new data label and parameters of the existing electronic device or sensor, and is compatible with the aircraft data bus line. The process of generating new data and outputting it in one direction ,
An aircraft data bus line connecting method characterized by being provided with. An aircraft equipped with an existing electronic device or sensor and an aircraft data bus line that transmits a signal from the existing electronic device or sensor in a predetermined data transmission format is different from the predetermined data transmission format. The process of installing a new electronic device or sensor that transmits data in the data transmission format, and
The process of interposing the embedded controller between the aircraft data bus line and the newly installed electronic device or sensor, and
Multiple signals are input from the new electronic device or sensor to generate new data in a data transmission format compatible with the aircraft data bus line, including a new data label and parameters of the existing electronic device or sensor. Then, in the process of storing the output program in the built-in controller in one direction ,
A data transmission format that inputs a plurality of signals from the new electronic device or sensor to the embedded controller, includes a new data label and parameters of the existing electronic device or sensor, and is compatible with the aircraft data bus line. The process of generating new data and outputting it in one direction ,
An aircraft data bus line connecting method characterized by being provided with. A process of detachably connecting a general-purpose computer equipped with a normal operation confirmation program for confirming whether or not the program performs a desired function to the embedded controller, and
A step of confirming whether or not the program performs a desired function on the general-purpose computer by using the normal operation confirmation program, and
The aircraft data bus line connecting method according to claim 3 or 4 , further comprising. A process of detachably connecting a function expansion medium containing a function expansion program that enables the newly generated data to be used by an existing electronic device or sensor to the embedded controller.
A step of extending the function of the existing electronic device or sensor so that the newly generated data can be used by using the function expansion program.
The aircraft data bus line connecting method according to claim 3 or 4 , further comprising. A step of detachably connecting a function expansion medium containing a function expansion program that enables the newly generated data to be used by an existing monitor or recording device to the embedded controller.
The function extension program is used to extend the function so that the existing monitor can display the newly generated data, or the recording device can record the newly generated data. And the process to do
The aircraft data bus line connecting method according to claim 3 or 4 , further comprising. The aircraft data bus line connection method according to any one of claims 4 to 7, wherein the aircraft data bus line of the predetermined data transmission format further includes MIL-1553 or ARINC standard.