CN109696899B

CN109696899B - Special quality comprehensive evaluation system for aircraft ARINC429 bus

Info

Publication number: CN109696899B
Application number: CN201710985729.2A
Authority: CN
Inventors: 刘妍; 陈曦; 赵宏旭; 王家林
Original assignee: Commercial Aircraft Corp of China Ltd; Shanghai Aircraft Manufacturing Co Ltd
Current assignee: Commercial Aircraft Corp of China Ltd; Shanghai Aircraft Manufacturing Co Ltd
Priority date: 2017-10-20
Filing date: 2017-10-20
Publication date: 2022-02-18
Anticipated expiration: 2037-10-20
Also published as: CN109696899A

Abstract

The invention provides a special quality comprehensive evaluation system for an aircraft ARINC429 bus, which comprises a controller, and a protocol layer test module, an electrical layer test module and a physical layer test module which are respectively connected with the controller, wherein the protocol layer test module detects the error rate and the packet loss rate of an ARINC429 bus signal based on an interface control file database, the electrical layer test module detects the electrical parameters of the ARINC429 bus signal according to related terms in an ARINC429 specification, and the physical layer test module tests the connectivity of an ARINC429 bus cable based on a spread spectrum time domain reflection method.

Description

Special quality comprehensive evaluation system for aircraft ARINC429 bus

Technical Field

The invention relates to a bus quality evaluation system, in particular to a special comprehensive quality evaluation system for an aircraft ARINC429 bus.

Background

With the development and progress of aeronautical technologies, electronic information, computer technologies, control technologies, etc., more and more electronic systems are being used widely due to their high efficiency, rapidity, and reliability. Civil aircraft must ensure safety and reliability, so the interaction of information between avionics systems and between some onboard sensors or other electronic devices becomes a big problem in aircraft design. The aviation data bus is used as a framework and a nerve of an avionic system and plays a vital role in improving the overall performance of the airplane.

In the development process of aviation buses, in order to improve the safety and reliability of the aviation buses, a series of standards and specifications are established, wherein civil airborne buses comprise ARINC-429/629, CSDB, STAN-AG-3838/3910, LTPB, FDDI, AFDX and the like, and military typical airborne data buses comprise MIL-STD-1553B, 1773, SCI, FC and the like. The ARINC429 is an aviation bus which is earlier in research and development and good in engineering application at present, has a series of advantages of simple and practical specification and definition, relatively easy design and maintenance, low design cost, good compatibility of electronic equipment and the existing avionics system and the like, and becomes one of important choices for researching and developing airplanes.

When the ARINC429 bus is installed or repaired, the quality of signals is important to ensure the normal transmission of relevant signals of the airplane, so that an ARINC429 bus signal evaluation system is required to complete the quality check of the ARINC429 bus signals so as to ensure the safe data transmission of the ARINC429 bus.

The research on the ARINC429 bus mainly focuses on the development of signal receiving boards and the monitoring of protocol layer data. Research on a receiving mode of an ARINC429 bus signal mainly focuses on hardware design, and data acquisition and analysis are realized by adopting different processing units such as ARM, DSP or FPGA. Research on ARINC429 bus data monitoring mainly focuses on protocol layer testing, and testing the quality and reliability of transmitted data according to bus specifications. The quality of bus data transmission is not limited to integrity on a protocol layer, for example, when some buses are tested by the protocol layer, the error rate is still in a safe range, but the electrical characteristics of signals of the buses are close to a critical state, and the bus cables still need to be repaired.

Disclosure of Invention

The technical problem to be solved by the invention is to provide a special comprehensive quality evaluation system for an aircraft ARINC429 bus, which can test the electrical characteristics of an ARINC429 bus signal and the on-off connectivity of the bus and really realize the monitoring of the transmission quality of the bus signal.

The system is mainly constructed on the basis of an NI PXI bus case, an independent high-speed controller and I/O board cards applied to different test modules. The PXI bus case provides communication connection between the controller and the test board card, and the controller is mainly responsible for logic control, data processing, board card driving and other functions.

According to the technical scheme of the invention, the special comprehensive quality evaluation system for the ARINC429 bus of the airplane comprises a protocol layer test module, an electrical layer test module and a physical layer test module. The system comprises a protocol layer testing module, an electrical layer testing module, a physical layer testing module and a physical layer testing module, wherein the protocol layer testing module is used for detecting the error rate and the packet loss rate of an ARINC429 bus signal based on an interface control file (ICD) database, the electrical layer testing module is used for detecting parameters such as the level, the rising edge and the falling edge of the bus signal, time delay and the signal-to-noise ratio according to relevant terms in an ARINC429 specification, and the physical layer testing module is mainly used for testing the connectivity of the bus cable based on an extended spectrum time domain reflection method and mainly used for detecting the on-off condition of the bus cable.

The protocol layer test module comprises a 429 bus transceiver board card and a 429 bus (protocol layer test bus). The 429 bus transceiver board is responsible for sending and receiving 429 bus data packets, and the 429 bus is responsible for data transmission.

The electric layer test module comprises a 429 bus transceiver board, an analog signal acquisition board and a 429 bus (an electric layer test bus). The 429 bus transceiver board is only used for sending 429 bus data, the analog signal acquisition board is responsible for carrying out high-speed sampling on the waveform of a bus signal, so that the electrical characteristic test of the waveform of the bus signal is carried out, and the 429 bus is responsible for data transmission.

(3) The physical layer test module comprises an arbitrary waveform sending board card, an analog signal acquisition board card, a 429 bus (a physical layer test bus) and a transfer box. The arbitrary waveform sending board card is used for generating independent pulses and test square waves, the analog signal acquisition board card is responsible for carrying out high-speed sampling on the test square waves or the test pulses, the 429 bus is responsible for data transmission, and the transfer box is responsible for setting the on-off connectivity of the bus.

The invention has the advantages that on the basis of the traditional protocol layer test, the test of an electrical layer and a physical layer is added, so that the bus test is not only limited to the transmission result of the bus signal any more, and the monitoring of the transmission quality of the bus signal is realized in a real sense.

Drawings

Other features and advantages of the present invention will be better understood by the following detailed description of the preferred embodiments when considered in conjunction with the accompanying drawings, in which:

FIG. 1 is a block diagram of a system for comprehensive assessment of the quality of an aircraft ARINC429 bus according to the invention; and

fig. 2 is a test flow chart of the aircraft ARINC429 bus dedicated quality comprehensive evaluation system according to the invention.

Detailed Description

The practice and use of the preferred embodiments according to the present invention are discussed in detail below in conjunction with the accompanying drawings. It should be understood, however, that the detailed description discussed is merely exemplary of specific ways to make and use the invention, and does not limit the scope of the invention. The description herein of the structural positions of the respective components such as up, down, left, right, top, bottom, etc. is not absolute, but relative. When the respective components are arranged as shown in the drawings, these direction expressions are appropriate, and when the positions of the respective components in the drawings are changed, these direction expressions are changed accordingly.

The comprehensive quality evaluation system special for the aircraft ARINC429 bus is shown in fig. 1 and mainly comprises an NI PXI bus chassis, a controller and an I/O board card. The PXI bus case provides communication connection between the controller and the test board card, and the controller is mainly responsible for logic control, data processing, board card driving and other functions.

The protocol layer test module comprises a 429 bus (or a protocol layer test bus) in which a 429 bus transceiver board is connected with a 429 bus transceiver board, wherein the 429 bus transceiver board is responsible for sending and receiving 429 bus data packets, and the 429 bus is responsible for data transmission. The protocol layer testing module mainly uses an ARINC429 bus transceiving board card to realize data transceiving, and further tests the bit error rate, the packet loss rate and the transmission rate of bus transmission data.

The electric layer test module comprises a 429 bus transceiver board, an analog signal acquisition board and a 429 bus (or an electric layer test bus), wherein the 429 bus transceiver board is connected with the analog signal acquisition board through 429 bus. The electrical layer testing module mainly uses an ARINC429 bus board card and an analog signal acquisition board card, wherein the 429 bus transceiver board card is only responsible for sending data, and the analog signal acquisition board card is responsible for acquiring data waveforms, so that the electrical parameters can be tested, such as level, edge, delay, signal-to-noise ratio and the like.

The physical layer test module comprises an arbitrary waveform transmitting board card, an analog signal acquisition board card, a 429 bus (or a physical layer test bus) and a transfer box, wherein the arbitrary waveform transmitting board card and the analog signal acquisition board card are connected through the 429 bus. The physical layer testing module mainly applies an arbitrary waveform generation board card and an analog signal acquisition board card, wherein the arbitrary waveform generation board card is used for sending square waves and pulse waves, and the acquisition board card is responsible for acquiring waveforms and realizes the judgment and the positioning of the connectivity faults of the bus cable according to a spread spectrum time domain reflection method.

The test flow of the aircraft ARINC429 bus special quality comprehensive evaluation system is shown in FIG. 2. Firstly, a user selects a mode, automatically selects a corresponding hardware board card according to different test mode systems, and then starts to guide the user to set test data. The test data is different depending on the mode selection.

The protocol layer test comprises test data parameter setting, test data sending, test data receiving, data analysis and data comparison.

The electrical layer test comprises test data parameter setting, test data sending, test data receiving and electrical characteristic analysis.

The physical layer test comprises square wave generation, square wave receiving, fault type judgment, pulse wave generation, pulse wave receiving and fault distance judgment.

For protocol layer and electrical layer testing, parameters for test data type, test data quantity, and test rate are first defined by the user. And then the system generates original data by calling an ICD database and drives a hardware board card to transmit. The data in the protocol layer test module is received by a digital board card (ARINC429 bus transceiver board card), and the controller is used for comparing the transmitted data with the received data, so as to calculate and analyze parameters such as bit error rate, packet loss rate and the like. And in the electrical layer test, data acquisition is completed through the analog signal acquisition board card, waveform reproduction is realized, and corresponding parameters such as level, edge, time delay, signal to noise ratio and the like are analyzed and extracted by the controller.

For physical layer testing, test data is automatically generated by the system. Firstly, sending the wave data by an arbitrary waveform generation board card, and receiving by an analog signal acquisition board card, thereby realizing the judgment of the fault type. If the fault exists, sending pulse data through the random waveform generation board card, and receiving the pulse data through the analog signal acquisition board card to further realize fault positioning.

While the technical content and the technical features of the specific embodiments of the invention have been disclosed, it is to be understood that various changes and modifications of the combinations of the features disclosed above and the features not explicitly shown herein can be made by those skilled in the art within the spirit of the invention, and the scope of the invention is not limited thereto. The above description of embodiments is intended to be illustrative, and not restrictive, and the scope of the invention is defined by the appended claims.

Claims

1. A special quality comprehensive evaluation system for an aircraft ARINC429 bus is characterized by comprising a controller, a protocol layer test module, an electrical layer test module and a physical layer test module which are respectively connected with the controller, and I/O (input/output) board cards applied to different test modules, wherein corresponding hardware board cards are automatically selected according to different test mode systems to guide a user to set test data, the protocol layer test module detects the error rate and the packet loss rate of an ARINC429 bus signal based on an interface control file database, the electrical layer test module detects the electrical parameters of the ARINC429 bus signal according to related terms in an ARINC429 specification, and the physical layer test module tests the connection of an ARINC429 bus cable based on an extended spectrum time domain reflection method;

the protocol layer test comprises the following steps: testing the error rate, the packet loss rate and the transmission rate; the electrical layer test comprises: level, edge, delay and signal-to-noise ratio tests; the physical layer test comprises the judgment and the positioning of the connectivity fault of the bus cable;

the protocol layer and the electrical layer are tested, and parameters of the type of test data, the quantity of the test data and the test rate are defined by a user; and in the physical layer test, test data is automatically generated by the system.

2. The aircraft ARINC429 bus-specific quality comprehensive assessment system according to claim 1, further comprising an NI PXI bus chassis providing communication connections between said controller and said protocol layer test module, said controller and said electrical layer test module, and said controller and said physical layer test module.

3. The aircraft ARINC429 bus-specific quality comprehensive evaluation system of claim 1 or 2, wherein the protocol layer test module comprises a 429 bus transceiver board and a protocol layer test bus formed by 429 bus, the protocol layer test bus is connected with the 429 bus transceiver board, the 429 bus transceiver board is responsible for transmitting and receiving 429 bus data packets, and the protocol layer test bus is responsible for data transmission.

4. The system of claim 3, wherein the electrical layer test module comprises a 429 bus transceiver board, an analog signal acquisition board and an electrical layer test bus formed by a 429 bus, wherein the 429 bus transceiver board is connected with the analog signal acquisition board through the electrical layer test bus, the 429 bus transceiver board is used for sending 429 bus data, the electrical layer test bus is used for data transmission, and the analog signal acquisition board is used for sampling 429 bus signal waveforms at high speed so as to test electrical characteristics of bus signal waveforms.

5. The system for comprehensively evaluating the quality special for the ARINC429 bus of the airplane as claimed in claim 4, wherein the physical layer test module comprises an arbitrary waveform transmitting board card, the analog signal collecting board card, a physical layer test bus formed by a 429 bus and a transfer box, wherein the arbitrary waveform transmitting board card and the analog signal collecting board card are connected through the physical layer test bus, the arbitrary waveform transmitting board card is used for generating independent pulses and test square waves, the analog signal collecting board card is responsible for sampling the test square waves or the test pulses at a high speed, the physical layer test bus is responsible for data transmission, and the transfer box is responsible for setting the on-off connectivity of the physical layer test bus.