CN108089975A - A kind of method of constructing environment Control System Software virtual testing environment - Google Patents
A kind of method of constructing environment Control System Software virtual testing environment Download PDFInfo
- Publication number
- CN108089975A CN108089975A CN201711174021.5A CN201711174021A CN108089975A CN 108089975 A CN108089975 A CN 108089975A CN 201711174021 A CN201711174021 A CN 201711174021A CN 108089975 A CN108089975 A CN 108089975A
- Authority
- CN
- China
- Prior art keywords
- control system
- environment
- environmental control
- interface
- buses
- 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.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/36—Preventing errors by testing or debugging software
- G06F11/3664—Environments for testing or debugging software
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/36—Preventing errors by testing or debugging software
- G06F11/3668—Software testing
- G06F11/3696—Methods or tools to render software testable
Abstract
The invention discloses a kind of methods of constructing environment Control System Software virtual testing environment, belong to mobile system software testing technology field.Including building comprehensive airborne electronic equipment grid configuration containing environmental control system first, and structure interface associated with the environmental control system, virtual target machine associated with the environmental control system is built afterwards, form embedded OS, and Simulation Control and display module are built according to above-mentioned network configuration, and structure peripheral equipment model library, the systematic fault model of institute is established afterwards, and development behavior chained library, to form the interface with the environmental control system and the embedded OS, finally integrate auxiliary testing tool, for carrying out the test of black box and whitepack to environmental control system software.In this way, in virtual testing environment or system, the test of environmental control system Airborne Software configuration item can independently and be fully completed, from the influence of winged guard system real running environment.
Description
Technical field
The invention belongs to mobile system software testing technology fields, and in particular to a kind of constructing environment Control System Software is empty
Intend the method for test environment.
Background technology
Integrated avionics system software and hardware integrated design technique obtains wide on the military-civil aircraft of modern various models
General application, environmental control system software (ECS softwares) realize each Member Systems centralized maintenance of aircraft and the function of management.
The research and development pattern of environmental control system software (ECS softwares) at present first carries out software totality or Outline Design first,
Proceed by again after hardware device reaches delivery status, research and development of software and tester carry out again software design and develop and unit
Unit test and software and hardware system integration testing and verification.
It is soft since integrated avionics system environmental control system software (ECS softwares) and hardware have very big correlation
Part configuration item is tested and system testing depends critically upon the crosslinked many airborne products of interface or system, and embedded software is caused to exist
Following problem is primarily present in exploitation and verification：
If a) conventionally, the test of environmental control system software (ECS softwares) configuration item is needed to wait and mutually shut down
After the completion of the exploitation and test of loading system hardware device, it can just carry out the Airborne Software after only submitting out available hardware device
Test job, the cycle of entire project is caused to be spun out；
B) in Airborne Software configuration item test phase, since hardware device resources are limited or hardware device cost is higher,
Cause Software Testing Project team that can not efficiently carry out dependence test work；
C) due to hardware device debugging stage early stage, in terms of may there are problems that design or model machine production, cause
When carrying out software configuration item test, can not effective district component software or hardware failure so that the testing efficiency of software is low；
D) in test Qualify Phase, based on real hardware environment, many abnormal feelings in environmental control system Software for Design
Condition (such as each Member Systems or fault mode of equipment) processing situations such as, it is difficult to by hardware environment carry out fully test and
Verification；
E) test Qualify Phase simultaneously in the software of multiple versions, due to only having a set of real hardware environment, form for
Multi version ECS softwares are tested, the unfavorable scene of test resource is competed simultaneously in same set of hardware testing system；
F) alternatively, only a set of real hardware environment often occur is researching and developing and verifying a certain version ECS software functions,
The state of another edition ECS software test cannot be carried out at the same time, has delayed test plan and software product installation plan carries out on time；
G) alternatively, the only physical varification platform in laboratory is in as outfield airborne equipment troubleshooting state, it is impossible to simultaneously
The state of ECS software tests is carried out, has delayed test plan and software product installation plan carries out on time；
H) further, install multi version ECS application states for outfield, from exploitation, experiment, outfield troubleshooting and inside and
There is the situation of test system keen competition at any time in each stage of external testing.
The content of the invention
To solve the above-mentioned problems, the present invention provides a kind of sides of constructing environment Control System Software virtual testing environment
Method establishes peripheral equipment Digital Simulation environment associated with environmental control system software (ECS softwares), while integrates maturation
Test analysis and management tool carry out white-box testing, the Black-box Testing of environmental control system software (ECS softwares) on this basis
And the integrated test facility of static analysis.This method mainly includes the following steps that：
Step 1: comprehensive airborne electronic equipment grid configuration of the structure containing environmental control system, the network configuration is extremely
Include less：
The first portion being made of air-conditioning system, hot gas anti-icing system, air supply system and pressure adjusting system；
The second portion being made of electronic device cooling system；
The Part III being made of Fault management subsystem；
Above-mentioned each system is connected by bus；
Step 2: associated with the environmental control system interface of structure, the interface include calculating data class interface,
It controls each in the network configuration in class interface, operating system interface, CPU programming classes interface, BSP plate grade interfaces and step 1
System interface；
Step 3: structure virtual target machine associated with the environmental control system, exploitation cpu instruction, BSP plate grade cores
Piece, I/O, interruption, clock analog functuion form embedded OS；
It is soft with environmental control system so as to according to testing requirement Step 4: using Ethernet simulation distribution formula data/address bus
The relevant peripheral emulation component of part can be dynamically joined to or exit virtual testing environment；
Step 5: according to step 1, Simulation Control and display module and structure are built comprising each in the first portion
First peripheral equipment model library of system, comprising the second peripheral equipment model library of each system in the second portion, include institute
State the 3rd peripheral equipment model library of each system in Part III；
Step 6: the systematic fault model of institute in establishment step five；
Step 7: the systematic dynamic link library of institute in development procedure five, and formed and the environmental control system and institute
State the interface of embedded OS；
Step 8: integrated auxiliary testing tool, for carrying out the test of black box and whitepack to environmental control system software.
Preferably, in the step 1, the bus is included in 429 buses, RS422 buses or 1553B buses extremely
Few one kind.
Preferably, in the step 1, environmental control system includes first environment control system and for backup
Second environment control system, first environment control system and second environment control system include binary channels.
Preferably, the binary channels in the first environment control system is connected between each other by HB6096 buses, institute
The binary channels in second environment control system is stated to connect by HB6096 buses between each other, the first environment control system with
The second environment control system is connected by HB6096 buses, and is passed through HB6096 buses and be connected to avionics system.
Preferably, the first environment control system and the second environment control system are connected by GJB289A buses
Pick electric management system.
Preferably, in the step 7, formed and to be connect with the environmental control system and the embedded OS
Further comprise classifying to interface or optimum organization after mouthful, the plug-in units of several realization difference in functionality are placed into same item
In mesh, to realize, multiple peripheral equipments emulate simultaneously.
Preferably, in the step 8, the auxiliary testing tool includes coverage rate test instrument, static analysis work
Tool, debugger and developing instrument.
It is an advantage of the invention that：
A) a kind of virtual testing environment towards sophisticated functions Airborne Software is provided for the first time, is met the completion of ECS softwares and is matched somebody with somebody
Put the demand (saving time and fund and personnel, flexible arrangement test plan) of item test；
B) comprising various test analysis, management tool on virtual testing environment, while the static state of ECS softwares can be met
Analysis/dynamic test, white-box testing/Black-box Testing method；
C) system-wide peripheral equipment normal function model library is not only established on virtual testing environment, but also is established
Fault model storehouse, the execution test for meeting all normal, borders and abnormality test use-case in ECS software configuration item test process will
It asks；
D) just because of establishing system-wide peripheral equipment normal function model library, and fault model storehouse is established, according to
Other later various aircraft airborne electronic system configurations effectively cut and optimize or extend, and can meet other special types and fly
The testing requirement of machine type environmental Kuznets Curves Airborne Software.
E) herein in virtual test system, the several new editions or liter of the follow-up military-civil various series of aircraft can also be tested
The environmental control system software (ECS softwares) of grade version, greatlys save fund, time and human resources.
Description of the drawings
Fig. 1 is the ring control of a preferred embodiment of the method for constructing environment Control System Software virtual testing environment of the present invention
Grid configuration schematic diagram；
Fig. 2 is the plane environmental control system grade interface relationship figure of embodiment illustrated in fig. 1 of the present invention；
Fig. 3 is the connection relation between the plane environmental control system of embodiment illustrated in fig. 1 of the present invention and avionics, electromechanics
Figure；
Fig. 4 is the environmental control system external interface figure of embodiment illustrated in fig. 1 of the present invention.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown is for only for ease of the description present invention and simplifies description rather than instruction or imply signified dress
It puts or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
The technical scheme is that：A kind of virtual testing environment is designed, comprising virtual target machine system, peripheral equipment just
Normal functional model library system, peripheral equipment fault mode model-base management system, distributed bus artificial network, test case injection,
Analysis and management system etc. provide the void of efficient white-box testing/Black-box Testing and static analysis/dynamic test for ECS softwares
Intend test environment.
This method mainly includes the following steps that：
Step 1: comprehensive airborne electronic equipment grid configuration of the structure containing environmental control system, the network configuration is extremely
Include less：
The first portion being made of air-conditioning system, hot gas anti-icing system, air supply system and pressure adjusting system；
The second portion being made of electronic device cooling system；
The Part III being made of Fault management subsystem；
Above-mentioned each system is connected by bus, with reference to figure 1.
It is understood that bus of the present invention includes 429 buses, RS422 buses or 1553B buses, alternate embodiment
In, also comprising other buses, it is described in detail in step 2.
Step 2: associated with the environmental control system interface of structure, the interface include calculating data class interface,
It controls each in the network configuration in class interface, operating system interface, CPU programming classes interface, BSP plate grade interfaces and step 1
System interface.
In the present embodiment, environmental control system includes first environment control system and is controlled for the second environment of backup
System, first environment control system and second environment control system include binary channels.As shown in Fig. 2, it is airplane environment control
System-level interface relational graph, ECSC1A softwares are the software in the first environment control system first passage in the present embodiment,
Communicated by HB6096 buses with the software (ECSC1B) in first environment control system second channel, by HB6096 buses with
In second environment control system first passage software (ECSC2A) communication, the difference is that, by GJB289A buses with
Software (ECSC2B) communication in second environment control system first passage, can combine Fig. 3, and four passages can pass through
GJB289A buses are in communication with each other, and are calculated with the electrical and mechanical comprehensive management computer EMP in Electric-machinery Management System and data acquisition
Machine DAP carries out two-way communication, equally, can also manage the power supply control in subsystem with power supply control by GJB289A buses
Manage computer EPMC and undercarriage control and the undercarriage control and position instruction control unit in position instruction subsystem
PDCU carries out two-way communication, returns to Fig. 2, in the present embodiment, ECSC1A also by HB6096 buses and cockpit exhaust valve and
Cargo hold exhaust valve connects, and by RS422 buses and the pressure sensor communication of cockpit and cargo hold, remaining signal passes through common
Rigid line connection.
Rigid line described here is, for example, the conducting wire using discrete magnitude analog signal transmission.
In the present embodiment, as shown in figure 3, the first environment control system passes through with the second environment control system
HB6096 buses connect, and pass through HB6096 buses and be connected to avionics system.Mainly it is connected to the aircraft accident of avionics system
Record collecting unit FDAU and atmosphere data machine ADC, and other systems (such as engine information warning system in avionics system
EICAS；Comprehensive warning system CAS；Multifunction display MFD；Centralized maintenance system CMS) then preferentially connected by avionics bus
To Electric-machinery Management System, then as described above, Electric-machinery Management System and the environmental control system of double remainings are integrated by GJB289A buses
Controller connects.
As shown in figure 4, environmental control system is by showing that class interface is connected with viewing hardware, by controlling class interface (example
Such as input/output interface) connection control hardware, by operating system interface attended operation system (such as RTOS systems), pass through
CPU programs class processor of interface connection hardware, connects BSP plate grade hardware by BSP plate grades interface (such as BIT interfaces), passes through
Bus interface connection electromechanics and avionics system.
It should be noted that in the present embodiment, therefore ring control subsystem, belongs to because being controlled using discrete magnitude
It controls in hardware, is connected by control interface.
Step 3: structure virtual target machine associated with the environmental control system, exploitation cpu instruction, BSP plate grade cores
Piece, I/O, interruption, clock analog functuion form embedded OS.
Target processor virtual kernel controls hardware, storage hardware, plate grade hardware etc. by distributed data bus with each
It is interconnected, the function of embedded type CPU is finally realized on virtual target machine.
It is soft with environmental control system so as to according to testing requirement Step 4: using Ethernet simulation distribution formula data/address bus
The relevant peripheral emulation component of part can be dynamically joined to or exit virtual testing environment.
Step 5: according to step 1, Simulation Control and display module and structure are built comprising each in the first portion
First peripheral equipment model library of system, comprising the second peripheral equipment model library of each system in the second portion, include institute
State the 3rd peripheral equipment model library of each system in Part III.
It is the Simulation Control of entire virtual testing environment and aobvious it is understood that design and simulation control and display module
Show center, can configure entire environmental control system software (ECS softwares) associated test system；Dynamically, visually show each
The data of a ECS software test cases implementation procedure can be managed and selected to record the data of each test case, and preserve.
In the present embodiment, peripheral equipment model library 1 is established, model library includes air supply system, air-conditioning system, hot gas anti-icing system, cockpit
The system model (normal function) of adjusting system is pressed, using the atmospheric environment simulation instrument of flight, is realized to aircraft atmospheric environment
Operation control, meets ECS softwares and avionics, Mechatronic Systems correlation function requirement, establishes peripheral equipment model library 2, model library bag
Electronic device cooling system correlation model (normal function) is included, meeting ECS softwares will with electronic device cooling system correlation function
It asks, establishes peripheral equipment model library 3, model library includes Fault management subsystem, meets ECS softwares and Fault management subsystem phase
Close functional requirement.
Step 6: according to peripherals model library 1,2,3, the fault model of all of above system is established, and is concentrated
Management, meets ECS software system tests border, failure use-case test execution demand.
Step 7: the systematic dynamic link library of institute in development procedure five, and formed and the environmental control system and institute
State the interface of embedded OS；In the present embodiment, exploitation more than subsystems dynamic link library (dll), and formed with
The standard interface of ECS softwares and embedded OS, is then classified or optimum organization, by several realization difference in functionality
Plug-in unit dll is placed into same project, it can be achieved that multiple peripheral equipment emulation simultaneously.
Step 8: comprehensive integration auxiliary testing tool, includes coverage rate test instrument (testbed softwares), static analysis
Instrument (COBOT wins software in storehouse), debugger, developing instrument (LabView) etc. carry out sortie software in virtual testing environment
While Black-box Testing, white-box testing, the test process such as static analysis and software quality metric can be also carried out.
On the basis of above, build ECS software testing systems application platform and build laboratory, carry out virtual environment survey
Examination.
Present invention structure totally digitilized virtual testing environment associated with environmental control system software (ECS softwares), point
Not by virtual target machine, Member Systems emulator, direct fault location and management emulator and test case management, analytical equipment etc.
Composition, this test system have following features.
A) in this virtual testing environment or system, the configuration of environmental control system Airborne Software can independently and be fully completed
Item test, from the influence of winged guard system real running environment；
B) tester need not be by real ECS softwares airborne computer equipment (target machine) and real airborne member system
Equipment of uniting and environmental excitation equipment；
It c), can be with the associated all Member Systems requirements of overlay environment control system using the virtual testing environment or system
Normal function and exception and fault mode function, test result there is certainty, the test philosophy of selection is reasonable, is not in
The situation that test result can not judge；
D) using the digitlization of this method structure or virtual test environment or system, can fully test or verification environment
The correctness and integrality of Control System Software (ECS softwares) Functional Design.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still
It can modify to the technical solution recorded in foregoing embodiments or which part technical characteristic is equally replaced
It changes；And these modifications or replacement, the essence of appropriate technical solution is not made to depart from the essence of various embodiments of the present invention technical solution
God and scope.
Claims (7)
- A kind of 1. method of constructing environment Control System Software virtual testing environment, which is characterized in that including：Step 1: comprehensive airborne electronic equipment grid configuration of the structure containing environmental control system, the network configuration at least wrap It includes：The first portion being made of air-conditioning system, hot gas anti-icing system, air supply system and pressure adjusting system；The second portion being made of electronic device cooling system；The Part III being made of Fault management subsystem；Above-mentioned each system is connected by bus；Step 2: structure interface associated with the environmental control system, the interface, which includes, calculates data class interface, control Each system in network configuration in class interface, operating system interface, CPU programming classes interface, BSP plate grade interfaces and step 1 Interface；Step 3: associated with the environmental control system virtual target machine of structure, develop cpu instruction, BSP plate grades chip, I/O, interruption, clock analog functuion form embedded OS；Step 4: using Ethernet simulation distribution formula data/address bus, so as to according to testing requirement, with environmental control system software phase The peripheral emulation component of pass can be dynamically joined to or exit virtual testing environment；Step 5: according to step 1, build Simulation Control and display module and structure includes each system in the first portion The first peripheral equipment model library, comprising the second peripheral equipment model library of each system in the second portion, include described 3rd peripheral equipment model library of each system in three parts；Step 6: the systematic fault model of institute in establishment step five；Step 7: the systematic dynamic link library of institute in development procedure five, and formed and the environmental control system and described embedding Enter the interface of formula operating system；Step 8: integrated auxiliary testing tool, for carrying out the test of black box and whitepack to environmental control system software.
- 2. the method for constructing environment Control System Software virtual testing environment as described in claim 1, which is characterized in that described In step 1, the bus includes at least one of 429 buses, RS422 buses or 1553B buses.
- 3. the method for constructing environment Control System Software virtual testing environment as described in claim 1, which is characterized in that described In step 1, environmental control system include first environment control system and the second environment control system for backup, first Environmental control system and second environment control system include binary channels.
- 4. the method for constructing environment Control System Software virtual testing environment as claimed in claim 3, which is characterized in that described Binary channels in first environment control system is connected between each other by HB6096 buses, in the second environment control system Binary channels is connected between each other by HB6096 buses, and the first environment control system is led to the second environment control system The connection of HB6096 buses is crossed, and passes through HB6096 buses and is connected to avionics system.
- 5. the method for constructing environment Control System Software virtual testing environment as claimed in claim 3, which is characterized in that described First environment control system and the second environment control system connect Electric-machinery Management System by GJB289A buses.
- 6. the method for constructing environment Control System Software virtual testing environment as described in claim 1, which is characterized in that described In step 7, formed after the interface with the environmental control system and the embedded OS further comprise to interface into The plug-in unit of several realization difference in functionality is placed into same project by row classification or optimum organization, multiple simultaneously outer to realize Peripheral equipment emulates.
- 7. the method for constructing environment Control System Software virtual testing environment as described in claim 1, which is characterized in that described In step 8, the auxiliary testing tool includes coverage rate test instrument, static analysis tools, debugger and developing instrument.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711174021.5A CN108089975A (en) | 2017-11-22 | 2017-11-22 | A kind of method of constructing environment Control System Software virtual testing environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711174021.5A CN108089975A (en) | 2017-11-22 | 2017-11-22 | A kind of method of constructing environment Control System Software virtual testing environment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108089975A true CN108089975A (en) | 2018-05-29 |
Family
ID=62172189
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711174021.5A Pending CN108089975A (en) | 2017-11-22 | 2017-11-22 | A kind of method of constructing environment Control System Software virtual testing environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108089975A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109799839A (en) * | 2018-12-24 | 2019-05-24 | 北京青云航空仪表有限公司 | A kind of automatic flight control assemblies |
| CN110879769A (en) * | 2019-10-16 | 2020-03-13 | 中国航空工业集团公司洛阳电光设备研究所 | Embedded system test environment construction method based on dynamically configurable framework |
| CN111176999A (en) * | 2019-12-25 | 2020-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Test platform construction method and test method for unmanned aerial vehicle flight control management software |
| CN111190821A (en) * | 2019-12-25 | 2020-05-22 | 中国航空工业集团公司西安飞机设计研究所 | Test platform construction method and test method of cabin door comprehensive management software |
| CN113433848A (en) * | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Remote measurement and control method and system for airplane secondary energy test |
| CN115774663A (en) * | 2022-09-15 | 2023-03-10 | 江苏瑞蓝自动化设备集团有限公司 | Optimization method, device, equipment and storage medium of LabVIEW test system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102968377A (en) * | 2012-12-13 | 2013-03-13 | 中国航空无线电电子研究所 | Virtual machine technique based airborne software system testing general platform |
| KR20140073367A (en) * | 2012-12-06 | 2014-06-16 | 정승화 | city environment control infrastructure build system |
| CN105045712A (en) * | 2015-07-15 | 2015-11-11 | 中国航空无线电电子研究所 | Test system for testing graphic processing module |
| CN106354642A (en) * | 2016-08-29 | 2017-01-25 | 中国航空工业集团公司西安飞机设计研究所 | Onboard central maintenance system software testing method and its system |
-
2017
- 2017-11-22 CN CN201711174021.5A patent/CN108089975A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20140073367A (en) * | 2012-12-06 | 2014-06-16 | 정승화 | city environment control infrastructure build system |
| CN102968377A (en) * | 2012-12-13 | 2013-03-13 | 中国航空无线电电子研究所 | Virtual machine technique based airborne software system testing general platform |
| CN105045712A (en) * | 2015-07-15 | 2015-11-11 | 中国航空无线电电子研究所 | Test system for testing graphic processing module |
| CN106354642A (en) * | 2016-08-29 | 2017-01-25 | 中国航空工业集团公司西安飞机设计研究所 | Onboard central maintenance system software testing method and its system |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109799839A (en) * | 2018-12-24 | 2019-05-24 | 北京青云航空仪表有限公司 | A kind of automatic flight control assemblies |
| CN110879769A (en) * | 2019-10-16 | 2020-03-13 | 中国航空工业集团公司洛阳电光设备研究所 | Embedded system test environment construction method based on dynamically configurable framework |
| CN110879769B (en) * | 2019-10-16 | 2024-01-26 | 中国航空工业集团公司洛阳电光设备研究所 | Method for constructing embedded system test environment based on dynamic configurable framework |
| CN111176999A (en) * | 2019-12-25 | 2020-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Test platform construction method and test method for unmanned aerial vehicle flight control management software |
| CN111190821A (en) * | 2019-12-25 | 2020-05-22 | 中国航空工业集团公司西安飞机设计研究所 | Test platform construction method and test method of cabin door comprehensive management software |
| CN111176999B (en) * | 2019-12-25 | 2023-07-21 | 中国航空工业集团公司西安飞机设计研究所 | Test platform construction method and test method of unmanned aerial vehicle flight control management software |
| CN113433848A (en) * | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Remote measurement and control method and system for airplane secondary energy test |
| CN115774663A (en) * | 2022-09-15 | 2023-03-10 | 江苏瑞蓝自动化设备集团有限公司 | Optimization method, device, equipment and storage medium of LabVIEW test system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108089975A (en) | A kind of method of constructing environment Control System Software virtual testing environment | |
| CN108089976A (en) | A kind of method for building flight management system software virtual testing environment | |
| CN106354642A (en) | Onboard central maintenance system software testing method and its system | |
| CN107992411A (en) | A kind of method for building task management system software virtual testing environment | |
| KR101355676B1 (en) | Flight control system for unmanned aerial vehicle of variable types | |
| US8659447B2 (en) | System for scheduling tasks to control the execution of warning procedures on an aircraft | |
| CN111190820B (en) | Configuration item test platform construction method and test method for display control software | |
| CN111176999B (en) | Test platform construction method and test method of unmanned aerial vehicle flight control management software | |
| CN105259788A (en) | Fault simulation method and system for flight control system | |
| CN103116287B (en) | Avionics equipment running environment dynamic simulating device and method | |
| CN107678958A (en) | A kind of method of testing for comprehensive parameters display system software | |
| CN102799709B (en) | System simulation test environment building and configuring system and method based on extensive markup language (XML) | |
| CN110884687A (en) | Semi-physical real-time simulation verification platform for PHM technology of electromechanical system | |
| CN109753430A (en) | A kind of interface test method of Ground Data Processing System | |
| Zhao et al. | Safety assessment of the reconfigurable integrated modular avionics based on STPA | |
| CN108073157A (en) | A kind of method for building Cabin Pressure Control System application software virtual testing environment | |
| CN112699036B (en) | Multi-partition multi-version airborne application software test case multiplexing method | |
| KR101976542B1 (en) | Method and system for controlling simulation via avionics simulation model | |
| CN111190821B (en) | Test platform construction method and test method of cabin door integrated management software | |
| CN108228404A (en) | A kind of domestic processor verification method based on aerospace applications | |
| Xu et al. | Cabin pressurization control system design of civil aircraft by model based systems engineering | |
| CN111044826B (en) | Detection method and detection system | |
| Lansdaal et al. | Boeing's 777 systems integration lab | |
| CN114398747B (en) | Communication navigation simulation loose coupling system of flight training simulator | |
| de Matos et al. | Using design patterns for safety assessment of integrated modular avionics |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180529 |
|
| RJ01 | Rejection of invention patent application after publication |