CN112214364B - Simulation method of IMB bus signals of C919 aircraft - Google Patents
Simulation method of IMB bus signals of C919 aircraft Download PDFInfo
- Publication number
- CN112214364B CN112214364B CN202010966227.7A CN202010966227A CN112214364B CN 112214364 B CN112214364 B CN 112214364B CN 202010966227 A CN202010966227 A CN 202010966227A CN 112214364 B CN112214364 B CN 112214364B
- Authority
- CN
- China
- Prior art keywords
- message
- simulation
- sfcp
- imb
- bus
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000004088 simulation Methods 0.000 title claims abstract description 92
- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000004458 analytical method Methods 0.000 claims abstract description 4
- 230000005540 biological transmission Effects 0.000 claims description 8
- 238000004891 communication Methods 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 9
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/22—Detection or location of defective computer hardware by testing during standby operation or during idle time, e.g. start-up testing
- G06F11/2205—Detection or location of defective computer hardware by testing during standby operation or during idle time, e.g. start-up testing using arrangements specific to the hardware being tested
- G06F11/221—Detection or location of defective computer hardware by testing during standby operation or during idle time, e.g. start-up testing using arrangements specific to the hardware being tested to test buses, lines or interfaces, e.g. stuck-at or open line faults
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Quality & Reliability (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention belongs to the technical field of flight test and test, and relates to a simulation method of an IMB bus signal of a C919 aircraft. The device adopted by the method has small volume, low cost, high efficiency and practicability, autonomously generates and outputs the IMB bus simulation signal, and can be used for building a semi-physical simulation system and checking the functions of the airborne acquisition device. The method comprises the following steps: step 1: the upper computer configures a system into a signal simulation mode through a USB2.0 interface; step 2: in a signal simulation mode, IMB bus simulation data are formed, and the IMB bus simulation data and simulation sending configuration information are packaged in SFCP information and sent to a simulation module through a USB2.0 interface; step 3: the simulation module receives the SFCP message, performs protocol analysis on the SFCP message, injects related faults, encapsulates the SFCP message into an IMB bus message, outputs the IMB bus message through the message sending circuit, and simultaneously gives a system state signal flag.
Description
Technical Field
The invention belongs to the technical field of flight test and test, and relates to a simulation method of an IMB bus signal of a C919 aircraft.
Background
The IMB (Inter-Model-Bus) Bus is a private Bus on the flight control system of the C919 aircraft, and the test of the Bus can only be carried out when the aircraft flies, so that the verification of the airborne acquisition equipment by using an IMB Bus signal simulation technology before the test is particularly important.
From the design angle of an IMB bus signal of aircraft flight control equipment, a foreign aviation equipment provider, namely a Honiswilt company, provides an IMB bus signal simulation method. The method is mainly used for simulating IMB bus signals during the production and development of the aircraft, and equipment adopted by the method is large in size and high in cost and is not suitable for being used during airborne testing.
The domestic research on IMB bus signal simulation is less, mainly takes an intervening monitoring mode as a main mode, namely monitoring the IMB bus signal of an aircraft flight control system, analyzing the IMB bus signal, and finally performing fault injection to obtain an IMB simulation signal expected by a user.
Disclosure of Invention
In view of this, the invention provides a simulation method for the IMB bus signal of the C919 aircraft, which adopts small equipment volume, low cost, high efficiency and practicality, autonomously generates and outputs the IMB bus simulation signal, and can be used for building a semi-physical simulation system and checking the functions of airborne acquisition equipment.
In order to solve the problems existing in the prior art, the technical scheme of the invention is as follows: the simulation method of the IMB bus signal of the C919 aircraft is characterized by comprising the following steps of: the method comprises the following steps:
step 1: the upper computer configures a system into a signal simulation mode through a USB2.0 interface;
step 2: in a signal simulation mode, IMB bus simulation data are formed, and the IMB bus simulation data and simulation sending configuration information are packaged in SFCP information and sent to a simulation module through a USB2.0 interface;
step 3: the simulation module receives the SFCP message, performs protocol analysis on the SFCP message, injects related faults, encapsulates the SFCP message into an IMB bus message, outputs the IMB bus message through the message sending circuit, and simultaneously gives a system state signal flag.
Further, the specific method in the step 2 comprises the following steps:
step 2.1: in the signal simulation mode, the upper computer forms IMB bus simulation data according to the IMB bus ICD file and simulation parameter configuration information;
step 2.2: acquiring simulation sending configuration information;
step 2.3: encapsulating IMB bus simulation data and sending configuration information in a communication protocol message of an upper computer and an FPGA;
step 2.4: and the SFCP message is sent to the simulation module through the USB2.0 interface.
Further, the specific method in the step 3 comprises the following steps:
step 3.1: the simulation module receives the SFCP message through the USB2.0 interface;
step 3.2: the IMB bus signal generating circuit analyzes the SFCP message and then injects related faults, and encapsulates the SFCP message into an IMB bus message according to an IMB protocol;
step 3.3: outputting the IMB bus message through a message sending circuit;
step 3.4: sending the simulation state signal flag to the LCD display module;
step 4: when the simulation state signal flag is 1, the LCD screen prompts to display 'in-simulation' state information.
Compared with the prior art, the invention has the following advantages:
according to the invention, the simulation signal of the IMB bus test port of the aircraft is output according to the IMB bus ICD file and parameter configuration information of the aircraft flight control system used for the airborne test, the simulation signal can be output with accurate timing, various faults can be injected, the types and the number of the signals can be freely configured, the function of acquiring the private IMB bus signal by the airborne equipment can be satisfied, and the invention has the characteristics of small equipment volume, low cost, high efficiency, practicability and the like.
Drawings
FIG. 1 is a schematic diagram of the working principle of a simulation technique of a proprietary IMB bus signal;
FIG. 2 is a schematic diagram of the operation of a simulation technique of proprietary IMB bus signals;
fig. 3 is an SFCP message format definition diagram.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The simulation method of the IMB bus signal of the C919 aircraft provided by the invention sends the SFCP message (comprising simulation data and configuration information) to the simulation module through the upper computer, the simulation module analyzes the SFCP message, then generates the IMB bus simulation signal according to the IMB protocol, and the system state display can be realized through the LCD display module. The system comprises an upper computer, a simulation module and an LCD display module, wherein the upper computer is connected with the simulation module, the simulation module is connected with the LCD display module, the simulation module comprises a USB interface circuit, a signal generating circuit and a message sending circuit, the upper computer is sequentially connected with the USB interface circuit, the signal generating circuit and the message sending circuit and outputs signals in 2 paths, and the power module supplies power to the system, as shown in figure 1.
The steps of the simulation method of the C919 aircraft IMB bus signal are shown in fig. 2:
step 1: the upper computer configures a system into a signal simulation mode through a USB2.0 interface;
step 2: in a signal simulation mode, IMB bus simulation data are formed, and the IMB bus simulation data and simulation sending configuration information are packaged in SFCP information and sent to a simulation module through a USB2.0 interface;
step 2.1: in the signal simulation mode, the upper computer takes parameter configuration information or parameter simulation information input by a user at a software interface as input quantity according to an IMB bus ICD file to form IMB bus simulation data;
step 2.2: the method comprises the steps of using transmission configuration information input by a user on a software interface as input quantity, and arranging the formed IMB simulation data according to a period;
step 2.3: respectively packaging the arranged IMB bus simulation data and other configuration information (such as time, message type, faults and the like) in communication protocol (SFCP) messages of an upper computer and an FPGA;
step 2.4: the SFCP message is sent to the simulation module through the USB2.0 interface;
step 3: the simulation module receives the SFCP message, performs protocol analysis on the SFCP message, injects related faults, encapsulates the SFCP message into a final IMB bus simulation message according to an IMB protocol, outputs the IMB bus simulation message through the message sending circuit, and simultaneously gives a system state signal flag.
Step 3.1: the simulation module receives the SFCP message through the USB2.0 interface;
step 3.2: the signal generating circuit analyzes the SFCP message and then injects related faults, and encapsulates the SFCP message into an IMB bus simulation message according to an IMB protocol;
step 3.3: and outputting the IMB bus simulation message through a message sending circuit.
Step 3.4: sending the simulation state signal flag to the LCD display module;
step 4: when the simulation state signal flag is 1, the LCD screen prompts to display 'in-simulation' state information.
The SFCP_message of the invention consists of three parts, namely SFCP_Length, SFCP_cmd and SFCP_Data.
1SFCP_Length:16bits, the SFCP message length.
2SFCP_cmd:16bits, which is a message command word, is composed of three parts, namely CH, PID and Value.
2.1CH: bit0 to bit1, which are transmission channel numbers, 0x01 represents channel 1;0x02 denotes channel 2.
2.2PID: bit2 to bit5 are command control words, and specific descriptions are shown in table 1.
2.3Value: bits 6 to 15 are configuration contents, and values are different according to the difference of PID values, and specific descriptions are shown in Table 1.
TABLE 1SFCP_Cmd configuration Table
TABLE 2 Fault type configuration
3SFCP_Data
According to different PID values, SFCP_Data is divided into three formats of time configuration, message configuration and Data configuration.
When pid=0x00, sfcp_data is the initial time of the IMB bus message transmission.
When pid=0x01, sfcp_data is an IMB bus messaging configuration table consisting of total number of cycles N, cycle number, IMB message number m within cycle number.
When pid=0x05, value is a period number, sfcp_data is IMB bus message transmission Data, and is composed of a message number imbsource_n, a message length imbsource_len, and a message IMBSource.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention.
Claims (3)
- Simulation method of IMB bus signals of a C919 aircraft, which is characterized in that: the method comprises the following steps:step 1: the upper computer configures a system into a signal simulation mode through a USB2.0 interface;step 2: in a signal simulation mode, IMB bus simulation data are formed, and the IMB bus simulation data and simulation sending configuration information are packaged in SFCP information and sent to a simulation module through a USB2.0 interface;the SFCP message comprises SFCP_Length, SFCP_cmd and SFCP_Data; SFCP_Length is SFCP message Length;SFCP_Cmd is a message command word, and comprises CH, PID and Value, wherein CH is a transmission channel number, 0x01 represents channel 1,0x02 represents channel 2, PID is a command control word, value is configuration content, PID values are different, and Value values are different;SFCP_Data is divided into three formats of time configuration, message configuration and Data configuration;when pid=0x00, sfcp_data is the initial time of the IMB bus message transmission;when pid=0x01, sfcp_data is an IMB bus message transmission configuration table, which is composed of a total cycle number N, a cycle number, and an IMB message number m in the cycle number;when pid=0x05, value is a period number, sfcp_data is IMB bus message transmission Data, and consists of a message number imbsource_n, a message length imbsource_len, and a message IMBSource;the simulation module comprises a USB interface circuit, a signal generating circuit and a message sending circuit, and the upper computer is sequentially connected with the USB interface circuit, the signal generating circuit and the message sending circuit and outputs signals in 2 paths;step 3: the simulation module receives the SFCP message, performs protocol analysis on the SFCP message, injects related faults, encapsulates the SFCP message into an IMB bus message, outputs the IMB bus message through the message sending circuit, and simultaneously gives a system state signal flag.
- 2. The method of simulating an IMB bus signal of an aircraft of claim 1, wherein: the specific method in the step 2 comprises the following steps:step 2.1: in the signal simulation mode, the upper computer forms IMB bus simulation data according to the IMB bus ICD file and simulation parameter configuration information;step 2.2: acquiring simulation sending configuration information;step 2.3: encapsulating IMB bus simulation data and sending configuration information in a communication protocol message of an upper computer and an FPGA;step 2.4: and the SFCP message is sent to the simulation module through the USB2.0 interface.
- 3. The method of simulating an IMB bus signal of an aircraft of claim 1, wherein: the specific method of the step 3 comprises the following steps:step 3.1: the simulation module receives the SFCP message through the USB2.0 interface;step 3.2: the IMB bus signal generating circuit analyzes the SFCP message and then injects related faults, and encapsulates the SFCP message into an IMB bus message according to an IMB protocol;step 3.3: outputting the IMB bus message through a message sending circuit;step 3.4: sending the simulation state signal flag to the LCD display module;step 4: when the simulation state signal flag is 1, the LCD screen prompts to display 'in-simulation' state information.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010966227.7A CN112214364B (en) | 2020-09-15 | 2020-09-15 | Simulation method of IMB bus signals of C919 aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010966227.7A CN112214364B (en) | 2020-09-15 | 2020-09-15 | Simulation method of IMB bus signals of C919 aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112214364A CN112214364A (en) | 2021-01-12 |
| CN112214364B true CN112214364B (en) | 2024-03-15 |
Family
ID=74048853
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010966227.7A Active CN112214364B (en) | 2020-09-15 | 2020-09-15 | Simulation method of IMB bus signals of C919 aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112214364B (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6297757B1 (en) * | 1999-02-11 | 2001-10-02 | Motorola, Inc. | Method and circuit for testing an analog-to-digital converter module on a data processing system having an intermodule bus |
| CN105914884A (en) * | 2016-05-13 | 2016-08-31 | 中国电力科学研究院 | One-to-many intelligent substation process layer virtual secondary equipment and implementation method |
| CN105974905A (en) * | 2016-05-10 | 2016-09-28 | 中国民航大学 | Simulated test system and method for single-particle overturn fault of aviation data bus |
| CN106936647A (en) * | 2017-04-26 | 2017-07-07 | 成都成电光信科技股份有限公司 | A kind of collocation method of new GJB289A buses |
| CN106982140A (en) * | 2017-03-31 | 2017-07-25 | 北京润科通用技术有限公司 | A kind of information flow emulation mode and system |
| CN107066243A (en) * | 2016-12-06 | 2017-08-18 | 西安航空学院 | A kind of parsing of general airborne-bus interface control document and packaging method |
| CN107942725A (en) * | 2017-11-24 | 2018-04-20 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of remote data concentrator ground simulation method |
| CN108958997A (en) * | 2018-05-23 | 2018-12-07 | 哈尔滨工业大学 | Universal serial bus fault simulation system and analogy method |
| CN209390084U (en) * | 2019-04-12 | 2019-09-13 | 北京旋极信息技术股份有限公司 | A kind of ARINC818 Bus simulator test device |
| CN110794709A (en) * | 2019-11-11 | 2020-02-14 | 长园深瑞继保自动化有限公司 | Method and system for simulating operation of BMS and PCS |
| CN110884687A (en) * | 2019-12-11 | 2020-03-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Semi-physical real-time simulation verification platform for PHM technology of electromechanical system |
| CN111125027A (en) * | 2019-12-24 | 2020-05-08 | 西安航空电子科技有限公司 | Aviation interface control file management system |
-
2020
- 2020-09-15 CN CN202010966227.7A patent/CN112214364B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6297757B1 (en) * | 1999-02-11 | 2001-10-02 | Motorola, Inc. | Method and circuit for testing an analog-to-digital converter module on a data processing system having an intermodule bus |
| CN105974905A (en) * | 2016-05-10 | 2016-09-28 | 中国民航大学 | Simulated test system and method for single-particle overturn fault of aviation data bus |
| CN105914884A (en) * | 2016-05-13 | 2016-08-31 | 中国电力科学研究院 | One-to-many intelligent substation process layer virtual secondary equipment and implementation method |
| CN107066243A (en) * | 2016-12-06 | 2017-08-18 | 西安航空学院 | A kind of parsing of general airborne-bus interface control document and packaging method |
| CN106982140A (en) * | 2017-03-31 | 2017-07-25 | 北京润科通用技术有限公司 | A kind of information flow emulation mode and system |
| CN106936647A (en) * | 2017-04-26 | 2017-07-07 | 成都成电光信科技股份有限公司 | A kind of collocation method of new GJB289A buses |
| CN107942725A (en) * | 2017-11-24 | 2018-04-20 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of remote data concentrator ground simulation method |
| CN108958997A (en) * | 2018-05-23 | 2018-12-07 | 哈尔滨工业大学 | Universal serial bus fault simulation system and analogy method |
| CN209390084U (en) * | 2019-04-12 | 2019-09-13 | 北京旋极信息技术股份有限公司 | A kind of ARINC818 Bus simulator test device |
| CN110794709A (en) * | 2019-11-11 | 2020-02-14 | 长园深瑞继保自动化有限公司 | Method and system for simulating operation of BMS and PCS |
| CN110884687A (en) * | 2019-12-11 | 2020-03-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Semi-physical real-time simulation verification platform for PHM technology of electromechanical system |
| CN111125027A (en) * | 2019-12-24 | 2020-05-08 | 西安航空电子科技有限公司 | Aviation interface control file management system |
Non-Patent Citations (3)
| Title |
|---|
| 1553B多路总线接口的FPGA设计;汤清华;曾婷婷;吴国安;;计算机测量与控制(第04期);全文 * |
| 民用飞机惯导信号仿真设计;金荣深;惠光飞;;现代工业经济和信息化(第09期);全文 * |
| 通用串行航空总线综合测试系统设计;宫海波;张振华;徐茜;;计算机测量与控制(第06期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112214364A (en) | 2021-01-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104820637B (en) | A kind of hand-held USB3.0 protocol analyzers | |
| CN105357070A (en) | FPGA-based ARINC818 bus analysis and test apparatus | |
| CN103869190A (en) | Real time simulation system-based power distribution terminal automatic closed-loop test platform | |
| CN112165415A (en) | 1553B bus control equipment, control system and control method | |
| CN105005015A (en) | Circuit fault simulation system based on hardware circuit fault injection | |
| CN105306154B (en) | Transmitting detection unit and its implementation based on FPGA | |
| CN111090556B (en) | System on chip and USB physical layer test method | |
| CN113467424A (en) | Special detection system for automatic flight control of airplane based on PC104 platform | |
| CN112214364B (en) | Simulation method of IMB bus signals of C919 aircraft | |
| Ma et al. | Sensors state monitoring based on labview and wireless nodes | |
| CN116796548A (en) | Digital modeling method for electric interface of single integrated management unit of satellite platform | |
| CN104866640A (en) | Full FIFO (first in, first out) circuit design method and universal test bench of method | |
| CN109143931B (en) | Integrated equipment with emission control and test functions | |
| CN112671101B (en) | Closed-loop test system and method for intelligent power transformation protection equipment with whole-screen cabinet access | |
| CN206450805U (en) | A kind of off-line test device of battery management unit | |
| CN215416349U (en) | Multifunctional star affair simulation ground inspection equipment | |
| CN206460161U (en) | electronic mutual inductor state collecting device | |
| CN103472387A (en) | General on-line test system and test method suitable for antifuse type FPGA | |
| CN113485879A (en) | Labview-based automatic testing method for calling vivado-tcl script | |
| CN202602670U (en) | IEC61850 detection platform of electric energy quality monitoring terminal | |
| CN207529166U (en) | A kind of environment cloud surveys the sensor data acquisition circuit of instrument | |
| CN213780953U (en) | DP/HDMI/VGA interface test fixture | |
| CN108020396B (en) | A kind of intelligent monitoring device and system suitable for wind-tunnel measurements system | |
| Chao et al. | Design of the measurement node of the grain quantity monitoring system based on the CAN-bus | |
| CN214151421U (en) | Digital quantity converter test equipment based on USB communication |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |