CN105653346B - A kind of general driver frame design method assisting avionics software development - Google Patents
A kind of general driver frame design method assisting avionics software development Download PDFInfo
- Publication number
- CN105653346B CN105653346B CN201410664408.9A CN201410664408A CN105653346B CN 105653346 B CN105653346 B CN 105653346B CN 201410664408 A CN201410664408 A CN 201410664408A CN 105653346 B CN105653346 B CN 105653346B
- Authority
- CN
- China
- Prior art keywords
- excitation
- data
- bus
- frame
- software
- 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
Abstract
The invention proposes a kind of general driver frame design methods for assisting avionics software development.It include: firstly, excitation acquisition module receives the excitation of hardware acquisition or software simulation by real bus or virtual bus and carries out data conversion.Secondly, configurable energized process module handles the excitation of acquisition according to the customized algorithm of user.Again, the excitation that excitation package module is completed according to the format encapsulation process in the library standard ICD.Finally, packaged excitation is sent to avionics system by real bus or virtual bus by excitation sending module.General driver frame design method of the invention can realize on PC, and complete docking for real bus and emulation bus and frame by the corresponding interface in frame.It solves the incompatibility problem between traditional software and hardware driver between different software driver, improves the versatility of frame；And data stimuli is handled by configuring a variety of different custom algorithms, enhance the flexibility of frame.
Description
Technical field
The invention belongs to avionics system field, it is related to having merged hardware driver and software driver and algorithm can
The general driver frame design method of configuration.
Background technique
With the development of avionics system, the requirement of avionics software development and test verifying is just stepped up.In order to
Guarantee software quality while shortening avionics software development cycle, and solves that development efficiency is low, debugging efficiency is low, time and space beam
It ties up, equipment fault and interface simulation device are difficult to the problems such as modifying.The exploitation of avionics software at present usually using virtual platform and
The mode that real hardware platform combines, the good transplantability of virtual platform promote the shortening of software development cycle；Hardware is flat
The authenticity of platform equipment is able to verify that the real-time and reliability of avionics software.But due to real hardware platform and virtual platform
Data stimuli producing method is different, and the excitation format that different software drivers generates is different.In addition user needs to acquisition
The excitation arrived carries out different processing.This has resulted in not simultaneous between hardware driver and software driver, software driver
Capacitive and the unicity of excited data processing.
Summary of the invention
Goal of the invention: providing a kind of general driver frame design method for assisting avionics software development, can be quick, low
The simulation different type avionics of cost motivates emulator.
A kind of technical solution: general driver frame design method assisting avionics software development, comprising:
S1: excitation acquisition module receives the excitation of hardware acquisition and the number of conversion cost frame identification by real bus
According to；The data of software simulation are received by virtual bus；
S2: configurable energized process module generates driver operation interface, the interface layout of the driver operation interface
And receptance function name is configured in xml table by user；The function response logic of the driver operation interface passes through use
Family is edited in dynamic library file, and the function response logic handles the data of excitation acquisition module, obtains amendment number
According to；
S3: the amendment data are packaged by excitation package module according to the format of avionics system ICD data word；
S4: excitation sending module is sent to avionics system by real bus for packaged data are converted, or will envelope
The data installed directly pass through virtual bus and are sent to avionics system.
The utility model has the advantages that general driver frame design method of the invention can be realized on PC, and pass through the phase in frame
Interface is answered to complete docking for real bus and emulation bus and frame.It solve between traditional software and hardware driver with it is difference soft
Incompatibility problem between part driver improves the versatility of frame；And by configuring at a variety of different custom algorithms
Data stimuli is managed, the flexibility of frame is enhanced.
Detailed description of the invention
Fig. 1 is the general driver frame design method flow chart of present invention auxiliary avionics software development.
Fig. 2 is avionics system ICD data word format chart.
Specific embodiment
A kind of general driver frame design method assisting avionics software development, comprising:
S1: excitation acquisition module receives the excitation of hardware acquisition and the number of conversion cost frame identification by real bus
According to；The data of software simulation are received by virtual bus；
S2: configurable energized process module generates driver operation interface, the interface layout of the driver operation interface
And receptance function name is configured in xml table by user；The function response logic of the driver operation interface passes through use
Family is edited in dynamic library file, and the function response logic handles the data of excitation acquisition module, obtains amendment number
According to；
S3: the amendment data are packaged by excitation package module according to the format of avionics system ICD data word；It is described
Avionics system ICD data word definition is as shown in Figure 2；
S4: excitation sending module is sent to avionics system by real bus for packaged data are converted, or will envelope
The data installed directly pass through virtual bus and are sent to avionics system.
As shown in Figure 1, in the present embodiment, the general driver Frame Design of auxiliary avionics software development of the invention
Method includes excitation acquisition module, configurable energized process module, excitation package module, excitation sending module.
In step sl, excitation acquisition module is responsible for the acquisition of external drive comprising two kinds of acquisition modes: receiving true
Bus data and reception virtual bus data.Two ways shares one group of common interface, in receive process can according to data come
Source Type mark is judged, determines reception mode.Real bus data can be by adding true board and according to this in PC
The API that board provides is obtained, through storage after conversion into common structural body；Virtual bus data can use based on memory
The emulation bus of mapped file directly stores after being obtained by external simulation software (such as Flsim or customized excitation generates panel)
Into common structural body.
In step s 2, configurable energized process module acquires step S1 and formatted data are packaged into structural body
In the incoming function response logic that can customize, general framework has arranged parameter, the return value of the function, developer
The diversity that directly collected excitation can be handled using the function and different algorithms is cooperated to realize that user can configure
Processing.To realize merging for user configuration and general framework, configurable energized process module can exist in the form of dynamic base,
Developer only need to carry out different algorithm configurations to the statement of the function according to general framework.
In step s3, excitation package module by treated in S2 excitation according to avionics system ICD data word format
Excitation encapsulation is carried out, the format by user's custom algorithm treated excited data according to avionics system ICD data word is made
It is forwarded, to make acquisition and treated excited data has certain sense in the operation of avionics software.With big destiny
For, label value is that 0x4A indicates that true air speed, source/destination or data are 0, indicates atmospheric engine 1, data bit 300 indicates vacuum
Speed value, state matrix are 3 expression normal datas.
In step s 4, excitation sending module by step S3 by being sealed according to avionics system ICD data word format
ICD excitation after dress is sent.The ICD after encapsulation can be motivated into number by the select button that driver operates user interface
According to by conversion be sent to real bus (by added in PC true board and according to the board provide API send) or will
Packaged data are sent directly to virtual bus, and (emulation bus that can use mapped file based on memory passes through external emulation
Software is sent).To be transmitted in avionics system by the ICD excitation after acquisition, processing, encapsulation.
The present invention is not limited to above-mentioned preferred forms, anyone can obtain other various shapes under the enlightenment of invention
The product of formula, however, make any variation in its shape or structure, it is all that there is technology identical or similar to the present application
Scheme is within the scope of the present invention.
Claims (1)
1. a kind of general driver frame design method for assisting avionics software development characterized by comprising
S1: excitation acquisition module receives the excitation of hardware acquisition and the data of conversion cost frame identification by real bus；It is logical
Cross the data that virtual bus receives software simulation；
S2: configurable energized process module generates driver operation interface, the interface layout and sound of the driver operation interface
Function name is answered to configure in xml table by user；The function response logic of the driver operation interface is existed by user
It is edited in dynamic library file, the function response logic handles the data of excitation acquisition module, obtains amendment data；
S3: the amendment data are packaged by excitation package module according to the format of avionics system ICD data word；
S4: excitation sending module is sent to avionics system by real bus for data that packaged this frame identifies are converted
System, or the data that packaged software is simulated directly are passed through into virtual bus and are sent to avionics system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410664408.9A CN105653346B (en) | 2014-11-19 | 2014-11-19 | A kind of general driver frame design method assisting avionics software development |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410664408.9A CN105653346B (en) | 2014-11-19 | 2014-11-19 | A kind of general driver frame design method assisting avionics software development |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105653346A CN105653346A (en) | 2016-06-08 |
| CN105653346B true CN105653346B (en) | 2019-01-01 |
Family
ID=56479089
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410664408.9A Active CN105653346B (en) | 2014-11-19 | 2014-11-19 | A kind of general driver frame design method assisting avionics software development |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105653346B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114486310A (en) * | 2021-12-31 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Dynamic simulation comprehensive test system and method for aircraft electromechanical management system |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5541863A (en) * | 1994-09-30 | 1996-07-30 | Rockwell International | Virtual integrated software testbed for avionics |
| CN1928877A (en) * | 2006-08-17 | 2007-03-14 | 电子科技大学 | Verification method for SOC software and hardware integration design |
| CN101174283A (en) * | 2007-12-03 | 2008-05-07 | 电子科技大学 | Software and hardware cooperating simulation platform based on network |
| CN101763443A (en) * | 2008-12-23 | 2010-06-30 | 江西洪都航空工业集团有限责任公司 | Avionics system digitalized design verification system and method |
| CN102968311A (en) * | 2012-12-13 | 2013-03-13 | 中国航空无线电电子研究所 | Onboard embedded software development platform |
| CN103065022A (en) * | 2013-01-24 | 2013-04-24 | 无锡华航电子科技有限责任公司 | Incentive model simulation platform for aerocraft electronic system |
| CN103116287A (en) * | 2013-01-22 | 2013-05-22 | 中国民航大学 | Avionics equipment running environment dynamic simulating device and method |
| CN104102526A (en) * | 2014-07-04 | 2014-10-15 | 中国西电电气股份有限公司 | Collaborative interface for co-simulation of PSCAD (power system computer aided design) with third-party simulation software or hardware |
-
2014
- 2014-11-19 CN CN201410664408.9A patent/CN105653346B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5541863A (en) * | 1994-09-30 | 1996-07-30 | Rockwell International | Virtual integrated software testbed for avionics |
| CN1928877A (en) * | 2006-08-17 | 2007-03-14 | 电子科技大学 | Verification method for SOC software and hardware integration design |
| CN101174283A (en) * | 2007-12-03 | 2008-05-07 | 电子科技大学 | Software and hardware cooperating simulation platform based on network |
| CN101763443A (en) * | 2008-12-23 | 2010-06-30 | 江西洪都航空工业集团有限责任公司 | Avionics system digitalized design verification system and method |
| CN102968311A (en) * | 2012-12-13 | 2013-03-13 | 中国航空无线电电子研究所 | Onboard embedded software development platform |
| CN103116287A (en) * | 2013-01-22 | 2013-05-22 | 中国民航大学 | Avionics equipment running environment dynamic simulating device and method |
| CN103065022A (en) * | 2013-01-24 | 2013-04-24 | 无锡华航电子科技有限责任公司 | Incentive model simulation platform for aerocraft electronic system |
| CN104102526A (en) * | 2014-07-04 | 2014-10-15 | 中国西电电气股份有限公司 | Collaborative interface for co-simulation of PSCAD (power system computer aided design) with third-party simulation software or hardware |
Non-Patent Citations (1)
| Title |
|---|
| 通用综合航电仿真激励系统设计与实现;郑宏民 等;《机械科学与技术》;20120331;第31卷(第3期);全文 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105653346A (en) | 2016-06-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR102647291B1 (en) | Systems, methods, and apparatus to generate an integrated modular architecture model | |
| CN100487709C (en) | Verification method for SOC software and hardware integration design | |
| US9063800B2 (en) | Automated method for decoupling avionics application software in an IMA system | |
| US7509614B2 (en) | Method and system for integrating cores in FPGA-based system-on-chip (SoC) | |
| CN112232000B (en) | Authentication system, authentication method and authentication device spanning multiple authentication domains | |
| CN106095719A (en) | There is the network function virtual platform of function link ability | |
| CN106156424B (en) | Simulation system | |
| CN105656712B (en) | A kind of RFID protocol uniformity test platform and its working method based on ZYNQ | |
| CN101093521A (en) | FPGA emulation device and method | |
| CN110531384A (en) | A kind of Galilean satellite signal imitation system and its analogy method | |
| CN114707236A (en) | Model-based virtual-real combined simulation test method | |
| CN110109794A (en) | A kind of bus verification method based on UVM | |
| CN102495552A (en) | Real-time simulation system oriented to space-borne electronic system | |
| CN106708764A (en) | Universal IO processing system for airborne avionic system | |
| CN105653346B (en) | A kind of general driver frame design method assisting avionics software development | |
| CN106991001A (en) | Radionavigation recognizes simulation system | |
| CN108345440A (en) | A kind of method and its device of the geometric figure auxiliary line of display addition | |
| CN104503737B (en) | A kind of unified Modeling platform | |
| CN103309783A (en) | Test method and device based on bus communication | |
| CN103051728A (en) | Remote-procedure calling method | |
| CN100433024C (en) | Software and hardware synergism communication method | |
| CN110263459B (en) | UVM verification acceleration method based on test sequence analysis | |
| CN202267736U (en) | General type digital printed circuit board functional test circuit | |
| CN104503803A (en) | Linux kernel and file system upgrading method | |
| CN107861803A (en) | Cpci bus RS422 communications driving method under a kind of XP systems based on interruption |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |