CN2748385Y - Comprehensive detection system for airplane-carried device - Google Patents
Comprehensive detection system for airplane-carried device Download PDFInfo
- Publication number
- CN2748385Y CN2748385Y CNU2004200904667U CN200420090466U CN2748385Y CN 2748385 Y CN2748385 Y CN 2748385Y CN U2004200904667 U CNU2004200904667 U CN U2004200904667U CN 200420090466 U CN200420090466 U CN 200420090466U CN 2748385 Y CN2748385 Y CN 2748385Y
- Authority
- CN
- China
- Prior art keywords
- airplane
- card
- carried device
- detection system
- test
- 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.)
- Expired - Lifetime
Links
Images
Abstract
The utility model relates to a comprehensive detection system for an airplane-carried device. The serviceability rate of the airplane-carried device is the key factor to ensure the normal flight of the airplane. The production manufacturer of the airplane-carried device used to directly provide a corresponding detection device whose major defects are complex operation, simplex function, long measuring cycle, and high cost. The utility model aims at providing a comprehensive detection system for the airplane-carried device which is good-sized and integrative. The comprehensive detection system for the airplane-carried device provides the airplane-carried device with integrated maintenance, troubleshooting, detection, and satisfies a plurality of airplane models, such as Boeing, Kongke, etc. The utility model provides a comprehensive detection system for the airplane-carried device, compising a main cabinet, a terminal block, a special test adapter, and an interface socket unit under test.
Description
Technical field
The utility model relates to a kind of check implement, relates in particular to a kind of airborne equipment comprehensive detection system.
Background technology
The serviceability rate of airborne equipment is the key factor that ensures the aircraft normal flight.Past is that airborne equipment production firm directly provides relevant detection equipment always, and main product is the manual check implement of single cover still.The major defect that exists in the use is that complicated operation, function singleness, test period are long, and expense is higher, can not satisfy the demand of present civil aviaton, air force, Lu Hang, Hainan Airlines far away.
The airborne equipment comprehensive detection system at home and abroad is an emerging project, and its purpose is exactly the problems that exist in the check implement of will solving over.At present, resemble large-scale synthesis check implements such as ATEC6000 in the world, it adopts the vxi bus technology, uses supporting software, the detection of finishing multiple airborne equipment that can be automatic/semi-automatic.Advantage is that test item is many, efficient is high, but also have price high, the maintenance troubleshooting in problems such as service efficiency is low.At home, the research-and-development activity of comprehensive detection system is in the starting stage.
Summary of the invention
The purpose of this utility model is to provide the airborne equipment comprehensive detection system of a kind of maximization, synthesization, can complete maintenance, troubleshooting and detection is provided and can satisfy different types of machines such as Boeing, Air Passenger airborne equipment.
The utility model provides a kind of airborne equipment comprehensive detection system, also claims airborne MCP (Modle Control Panel) special inspecting equipment, and the main technology that adopts has gpib bus, PXI bus, vxi bus etc.Concrete tested object has piece number: 4051601-932,4051601-935,4051601-936,4051601-937,4051601-938,4051601-939,4051601-940 etc.This integrated test system is simulated its required ARINGC 429 bus signals, synchronous/as to revolve varied angle signal, discrete magnitude signal etc., and is received the various signals of handling MCP output according to the testing requirement of UUT.Adopt interactive operation interface to finish automatic (S. A.) test function of mode control panel system.
The present invention has has mainly researched and developed automatic guidance, has detected the maintenance process of software system, ARINC429 bus signals simulator, the exploitation of synchronizing signal simulator, automatic control circuit and airborne mode control panel.
The invention provides a kind of airborne equipment comprehensive detection system, it comprises mainframe box, terminal clamp, special test adapter and interface socket measured piece, mainframe box comprises keyboard, mouse, CPU, telltale, chopping machine, the ARINC429 bus card, SDDS synchronizing signal card and AX5488 card, terminal clamp comprises digital oscilloscope, digital multimeter and bus adapter, the special test adapter comprises signal adapter circuit and modulate circuit, keyboard wherein, mouse, telltale, chopping machine, the ARINC429 bus card, SDDS synchronizing signal card all links to each other with CPU with the AX5488 card, ARINC429 bus card wherein, SDDS synchronizing signal card, the AX5488 card, digital oscilloscope all links to each other with bus adapter with digital multimeter, bus adapter wherein links to each other with the special test adapter, and the special test adapter links to each other with the interface socket measured piece.
For the signal that guarantees system's distinct interface, cable all can insert general test facility and need not to change the general test facility circuit, test macro adopts the special test adapter to connect measurand and general test facility.The special test adapter comprises signal adapter circuit (relay switch array) and modulate circuit, the signal adapter circuit switches by relay, each parts of system both can be interconnected by former complete machine connection mode, arbitrary parts can be inserted test circuit separately again.When switch arrays n-1 and switch arrays n '-1 closure and switch arrays n-2 and switch arrays n '-2 open, can pass through one group of lead direct connection between parts n and the n ', by this mode each parts is communicated with by former complete machine connection mode.If when the switch arrays n-1 of only closed certain parts n and switch arrays n-2, the cable of these parts is connected to the signal adapter output interface by the signal adapter input interface, can make the interface of unit under test be connected to modulate circuit by universal test interface by the control relay action like this.
Modulate circuit will be adjusted to suitable amplitude from the straight signal of friendship of the next varying level of special test interface, send into circuitry for signal measurement.
Interface socket measured piece in the hardware system: be 4051601-932,4051601-935,4051601-936,4051601-937,4051601-938,4051601-939,4051601-940.
The invention has the beneficial effects as follows: the present invention can finish maintenance, troubleshooting, the Performance Detection of MCP, its advanced automatic guidance function, sophisticated software system, guaranteed real-time, accurate, the accurate detection of airborne MCP, the present invention has self-checking function, can guarantee that system self works reliably.Use airborne equipment comprehensive detection system of the present invention, can improve maintenance, detection efficiency, guarantee the integrity of army, civil aviaton's equipment, ensure aircraft safety, high efficiency flight.Native system extends to Civil Aviation System, system of air force or the like.Can satisfy air unit, air force's repair plant, civil aviaton's engineering, civil aviaton's boat and repair the maintenance demand of unit such as factory airborne MCP.Particularly airborne MCP extensively equips our troops, the various aircraft of civil aviaton, is airborne High Value Unit, and annual maintenance cost is very high.Past is sent in a large number and repaiies abroad, the cost of repair height, and the cycle is long, repaiies the back service and is difficult to guarantee.Of the present invention succeeding in developing can be improved domestic maintainability, saves a large amount of foreign exchanges, has good society and economic benefit.
Description of drawings
Fig. 1 is the system software block diagram
Fig. 2 is a software flow pattern
Fig. 3 is a mode control panel test system configurations schematic diagram
Fig. 4 is the structural representation of special test adapter
The specific embodiment
Tested " mode control panel " product by the test of this test equipment has: the test of 4051601-932,4051601-936,4051601-937,4051601-938,4051601-939,4051601-940.
After entering system test software, at first enter from detecting: by gpib bus instrument, switch matrix, digital I/O card, ARINC429 I/O card, SDDS I/O card etc., and call test software self-checking function module, realize the detection certainly of test macro, and after the System self-test success, automatically access main test program, the test program of reference pattern control panel CMM is finished test automatically.
When measured piece 4051601-932 carries out trouble diagnosing with the test program of " mode control panel " CMM of MCP integrated test system, its failure code is shown as:
2 road ARINC429 quantitative data inputs, the output of 1 road ARINC429 data have fault.
With reference to the requirement of CMM test program, software calls ARINC429 I/O function by ARINC429 I/O control card, make test product 4051601-932 very quick service return to work do normal.
Embodiment 2
When measured piece 4051601-937 carries out trouble diagnosing with the test program of " mode control panel " CMM of MCP integrated test system, its failure code is shown as:
The input of 2 tunnel synchronizing signals, the output of 4 tunnel synchronizing signals has fault.
When reprocessing, according to the CMM test program, software transfer synchronizing signal transmitting-receiving control function, and under the cooperation of synchronizing signal card feeding-discharging, realize the synchronizing signal input of MCP and the function that output is tested simultaneously.Make on time finishing that test product 4051601-937 guarantees both quality and quantity, and reach the requirement of mode control panel CMM.
Embodiment 3
When measured piece 4051601-939 carries out trouble diagnosing with the test program of " mode control panel " CMM of MCP integrated test system, its failure code is shown as:
Faults such as the input of 2 road GND/OPEN discrete magnitudes, the input of 2 road 28/19/12VDC discrete magnitudes, 4 road 26VAC/OPEN input.
Detection with desired discrete magnitude incoming signal in the CMM test program etc., test software is by DI/O control program, gpib bus order, the signal that MCP is required is imported by switch matrix, is finished the automatic detection of incoming signal simultaneously by avometer, oscp.Reprocess product thereby finish very soon, satisfy the requirement of mode control panel CMM.
Embodiment 4
When measured piece 4051601-940 carries out trouble diagnosing with the test program of " mode control panel " CMM of MCP combined test stand, failure code is shown as:
The fault of the output of 2 road GND/OPEN discrete magnitudes, the output of 1 road 28VDC/OPEN discrete magnitude, 2 road 28/19/12VDC discrete magnitude outputs etc.:
Adopt the detection of desired discrete magnitude output signal in the CMM test program etc., test software is by DI/O control program, gpib bus order, the signal that MCP is required is imported by switch matrix, is finished the automatic detection of output signal simultaneously by avometer, oscp.Make measured piece 4051601-940 fulfil the task of reprocessing ahead of schedule.
By the example of above several test products test, comprehensive, advanced, the trouble diagnosibility that has embodied MCP mode control panel integrated test system by force, the degree of automation advantages of higher, test result satisfies the requirement of CMM fully.
Claims (1)
1, a kind of airborne equipment comprehensive detection system, it is characterized in that it comprises mainframe box, terminal clamp, special test adapter and interface socket measured piece, mainframe box comprises keyboard, mouse, CPU, telltale, chopping machine, the ARINC429 bus card, SDDS synchronizing signal card and AX5488 card, terminal clamp comprises digital oscilloscope, digital multimeter and bus adapter, the special test adapter comprises signal adapter circuit and modulate circuit, keyboard wherein, mouse, telltale, chopping machine, the ARINC429 bus card, SDDS synchronizing signal card all links to each other with CPU with the AX5488 card, ARINC429 bus card wherein, SDDS synchronizing signal card, the AX5488 card, digital oscilloscope all links to each other with bus adapter with digital multimeter, bus adapter wherein links to each other with the special test adapter, and the special test adapter links to each other with the interface socket measured piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2004200904667U CN2748385Y (en) | 2004-09-24 | 2004-09-24 | Comprehensive detection system for airplane-carried device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2004200904667U CN2748385Y (en) | 2004-09-24 | 2004-09-24 | Comprehensive detection system for airplane-carried device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2748385Y true CN2748385Y (en) | 2005-12-28 |
Family
ID=35719877
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2004200904667U Expired - Lifetime CN2748385Y (en) | 2004-09-24 | 2004-09-24 | Comprehensive detection system for airplane-carried device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2748385Y (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102609800A (en) * | 2010-12-06 | 2012-07-25 | 波音公司 | Rapid rework analysis system |
| CN102721835A (en) * | 2012-07-03 | 2012-10-10 | 航天科工防御技术研究试验中心 | Test adapter |
| CN101815973B (en) * | 2007-08-20 | 2014-06-25 | 埃尔塞乐公司 | System for controlling at least one actuator for thrust reverser cowlings on a turbojet engine and method for testing said system |
| CN105913754A (en) * | 2016-06-21 | 2016-08-31 | 中国民航大学 | Circuit-level virtual maintenance teaching platform for aviation airborne electronic equipment |
| CN112046782A (en) * | 2020-09-16 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Single-engine fault elimination method for double-engine airplane |
-
2004
- 2004-09-24 CN CNU2004200904667U patent/CN2748385Y/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101815973B (en) * | 2007-08-20 | 2014-06-25 | 埃尔塞乐公司 | System for controlling at least one actuator for thrust reverser cowlings on a turbojet engine and method for testing said system |
| CN102609800A (en) * | 2010-12-06 | 2012-07-25 | 波音公司 | Rapid rework analysis system |
| CN102609800B (en) * | 2010-12-06 | 2017-08-15 | 波音公司 | Quick correction analysis system |
| CN102721835A (en) * | 2012-07-03 | 2012-10-10 | 航天科工防御技术研究试验中心 | Test adapter |
| CN102721835B (en) * | 2012-07-03 | 2014-06-04 | 航天科工防御技术研究试验中心 | Test adapter |
| CN105913754A (en) * | 2016-06-21 | 2016-08-31 | 中国民航大学 | Circuit-level virtual maintenance teaching platform for aviation airborne electronic equipment |
| CN112046782A (en) * | 2020-09-16 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Single-engine fault elimination method for double-engine airplane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201757767U (en) | General comprehensive automatic test system of airplane electronic part | |
| CN102092477B (en) | Device and method for automatic test and fault diagnosis of plane audio integrated system | |
| CN102184749B (en) | A kind of automatic test approach of DCS switch board | |
| CN109541353B (en) | Distribution automation detecting system | |
| CN109324601A (en) | The test platform of robot controller or control system based on hardware in loop | |
| CN103336194A (en) | Integrated automatic test system of on-board computer of civilian airliner | |
| CN102662112A (en) | Aircraft avionics ground test system based on PXI bus and Lab Windows Cvi | |
| CN204945356U (en) | A kind of Calibration for Special Testing Equipment platform | |
| CN201072597Y (en) | Automatic detection instrument for aviation electronic flight instrument | |
| CN106443311A (en) | Conduction and insulation test system and method of large aircraft automatic system | |
| CN101726414A (en) | Method and system thereof for measuring trial run parameter of aeroengine | |
| CN109189046A (en) | A kind of large aircraft Mechatronic Systems all-around test stand | |
| CN103699017A (en) | Simulation test system and simulation test method for interface equipment of simulator in nuclear power station | |
| CN112711829A (en) | Intelligent substation secondary equipment batch production intelligent maintenance system | |
| CN2869838Y (en) | Vehicle-carried apparatus comprehensive detecting system | |
| CN2748385Y (en) | Comprehensive detection system for airplane-carried device | |
| CN104793097A (en) | Automatic unmanned aerial vehicle cable net testing system and testing method | |
| CN203422426U (en) | Universal comprehensive automatic test system of airborne computer of civilian airliner | |
| CN201335775Y (en) | Airborne equipment comprehensive detection system | |
| CN207346123U (en) | A kind of testboard for the test of airplane data acquisition component | |
| CN107346128A (en) | Automated testing method and system for lock control plate | |
| CN115729217A (en) | Test system for controlling full link of thyristor converter valve | |
| CN109870993A (en) | A kind of automotive electronics electronic control unit testing system | |
| CN114115187A (en) | General detection platform and detection method for automatic airplane driving control system | |
| CN102637034A (en) | Composite signal detecting system and detecting method based on CAN (Controller Area Network) configuration |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CX01 | Expiry of patent term |
Expiration termination date: 20140924 Granted publication date: 20051228 |