CN106742048A - A kind of Aircraft landing gear system RS422 bus datas verification method and device - Google Patents
A kind of Aircraft landing gear system RS422 bus datas verification method and device Download PDFInfo
- Publication number
- CN106742048A CN106742048A CN201611014053.4A CN201611014053A CN106742048A CN 106742048 A CN106742048 A CN 106742048A CN 201611014053 A CN201611014053 A CN 201611014053A CN 106742048 A CN106742048 A CN 106742048A
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- Prior art keywords
- control unit
- bus
- landing gear
- sensor
- gear
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- 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
Abstract
The invention discloses a kind of Aircraft landing gear system RS422 bus datas verification method and device, comprising a normally closed switch, two RS422 bus transceivers and a message handler, the working condition and parameter current of two equipment room RS422 bus data prevailing transmission landing gear positions and equipment in Landing Gear System, by the reception RS422 bus datas between two mutually redundant control units, reconstruct and transfer, when can verify that landing gear position and control unit Parameters variation, whether the response condition of whole system meets design requirement.Real-time Collection equipment room bus data of the present invention, it is ensured that the security and integrality of system checking.
Description
Technical field
The present invention relates to undercarriage ground test field, particularly a kind of Aircraft landing gear system RS422 bus datas are tested
Card method and device.
Background technology
At present, to aircraft takeoffs and landings frame control system checking work, it is necessary to undercarriage carries out folding and unfolding work, by undercarriage
Verified in diverse location simulated failure state, this kind of verification method has the following disadvantages：（1）, checking need of work undercarriage
Multiple folding and unfolding work is done, the cycle is more long；（2）, need to carry out position sensor disassembling section in verification process, operation it is cumbersome and
There is personnel's potential safety hazard（3）, comprehensive verification cannot be carried out to landing gear position sensor rationality；（4）, undercarriage cannot be verified
When control unit breaks down, Landing Gear System carries out the working condition of standby switching.
The content of the invention
The technical problems to be solved by the invention are, in view of the shortcomings of the prior art, providing a kind of Aircraft landing gear system
RS422 bus datas verification method and device.
In order to solve the above technical problems, the technical solution adopted in the present invention is：A kind of Aircraft landing gear system RS422 is total
Line data verification method, using two RS422 bus transceivers, the bus communication line between two RS422 bus transceivers
A normally closed switch is connect on road；Two RS422 bus transceivers are connected with message handler；Distinguish at bus communication circuit two ends
Connect No. 1 control unit and No. 2 control units；No. 1 control unit and No. 2 control units are connected with landing gear position sensor；
The method includes：
The sampling period of message handler configuration RS422 bus transceivers is 10ms, and baud rate is 9600, counts a sampling week
The interim byte number for retrieving, effective word joint number is less than 9 bytes, then meet transmission demand；More than 9 bytes, then baud rate is configured
It is 19200, the byte number retrieved in one sampling period of statistics, effective word joint number is less than 21 bytes, then meet transmission demand；
Message handler changes the position sensing that No. 1 control unit or No. 2 control units are gathered by RS422 bus transceivers
Device signal, is modified signal transmission to No. 2 control units, by No. 2 control units by RS422 buses by No. 1 control unit
The different parameters for being modified signal transmission to No. 1 control unit, simulating landing gear position sensor, when No. 1 control unit inspection
Measure position sensor display undercarriage to receive entirely, No. 2 control unit position sensors are modified during to complete putting down, control unit
Report failure；When No. 1 control unit detects position sensor display undercarriage just in folding and unfolding centre position, No. 2 control unit inspections
Measure position sensor display undercarriage in place when, control unit drive undercarriage start instruction stop and report failure；
No. 2 bus transceivers of control unit of configuration are in disabled status, and now RS422 bus transceivers pass through message handler
No. 2 bus datas of control unit of simulation, acquiescence undercarriage is in down state, operates folding and unfolding joystick to retracted position,
Message handler is simulated nose-gear bottom lock sensor and is unlocked successively by RS422 buses, main landing gear bottom lock sensor
Unlock, the upper lock sensor of nose-gear is locked, and the upper lock sensor of main landing gear is locked, in the process No. 2 control units
Magnetic valve output interface drives nose-gear down lock unlocking valve, main landing gear down lock unlocking valve, in nose-gear receipts successively
Valve, main landing gear receives upper valve conducting, then meet and receive upper demand；
To extended position, message handler simulates nose-gear uplock to operation folding and unfolding joystick successively by RS422 buses
Sensor is unlocked, and the upper lock sensor of main landing gear is unlocked, and nose-gear bottom lock sensor is locked, and main landing gear down lock is passed
Sensor is locked, and No. 2 control unit magnetic valve output interfaces drive nose-gear uplock unlocking valve successively in the process, lead
Fall frame uplock unlocking valve, and nose-gear puts down valve, and main landing gear puts down valve conducting, then meet and put down demand.
Described information processor is connected with visualization device.
Present invention also offers a kind of Aircraft landing gear system RS422 bus datas checking device, including with bus communication
Two 422 bus transceivers of connection, are connected to one often on the bus communication circuit between two RS422 bus transceivers
Make and break is closed；Bus communication circuit two ends connect No. 1 control unit and No. 2 control units respectively；No. 1 control unit and No. 2 controls are single
Unit is connected with landing gear position sensor；Described information processor is connected with visualization device
Compared with prior art, the advantageous effect of present invention is that：It is of the invention effectively to shorten Landing Gear System proving period；
The sensor and control unit data that bus is transmitted are controllable in real time, can simulate various working；Checking work is in kind imitative by half
Very, it is to avoid the potential safety hazard produced by undercarriage control and sensor dismounting.
Brief description of the drawings
Fig. 1 is bus verification frame diagram；
Fig. 2 is normal authentication frame diagram；
Fig. 3 is that bus reconstructs validation framework figure；
Fig. 4 single channel bus verification frame diagrams.
Specific embodiment
The present invention includes normally closed switch, two RS422 bus transceivers and a message handler, and normally closed switch is put
In on equipment room bus communication circuit, by closure with disconnect controlling bus verification mode, as shown in Figure 1.
Normally closed switch is closed, and two equipment room communication bus data are directly accessed corresponding device, and bus receiver is received simultaneously
Connection bus data is simultaneously transmitted to message handler, and message handler will gather signal output to visualization device, and checking data are
It is no consistent with default electric interfaces parameter, as shown in Figure 2.
Normally closed switch disconnects, two bus transceivers of communication bus data access, the control unit number of buses that will be collected
According to transmitting to message handler, message handler is adjusted to the parameter in bus data, analog sensor or equipment state
Parameter, then information after treatment is exported to corresponding another equipment by bus transceiver, as shown in Figure 3.
Bus reconstruct verification method mainly verifies following several respects content：
1. the sampling period of RS422 bus transceivers is configured by message handler, by the RS422 bus datas to collecting
Frame head is retrieved, the frame head number retrieved in one sampling period of statistics, calculates the actual transmitting-receiving cycle of RS422 communication buses
With byte number, the total amount of byte that one second time internal bus can be received and dispatched is calculated, verify whether total amount of byte meets requirements.
2. the position sensor signals that No. 1 or No. 2 control units are gathered are changed by message handler, and exported to another
Platform control unit, No. 1 and No. 2 control units are adopted position sensor and are backuped each other in same position, by RS422 buses with it is another
One equipment is communicated, the sensor signal word and status word that can be gathered to RS422 bus transceivers by message handler
Modify and export the different parameters that landing gear position sensor is simulated to another control unit, checking undercarriage control
Whether system meets demand for control.
Preceding of simulation, Zuo Zhuqi, right master play wheel set sensor, and left and right has been led into 3 sensings that 4 masters take turns set sensor
Device parameter is set to ground connection, and state is set to normally, and the master of two control unit outputs of checking plays wheel load and should be the state of ground；Will
1 sensor parameters that left master plays 2 masters wheel set sensor are set to ground connection, and state is normal, and another state is set to
1 sensor parameters that right master plays 2 masters wheel set sensor are set to ground connection by failure, and state is normal, another state
Failure is set to, the master of two control unit outputs of checking plays wheel load and should be the state of ground；Wheel set sensor will be played before preceding 2
Parameter is set to ground connection, and state is set to normally, to have led 4 masters wheel set sensor any two and be set to ground connection and state
Normally, verify that the master of two control unit outputs plays wheel load and should be the state of ground.
Risen before simulation receive upper sensor, preceding put down sensor, left master rise receive upper sensor, left master rise put down sensor,
Right master plays the upper sensor of receipts, right master and rises and put down sensor, and whether access control unit can accurately indicate landing gear position.
Some undercarriage stowage position and extended position sensor are simulated while in place, whether access control unit can be reported
Abnormal failure information.
In the state of the activation of folding and unfolding joystick, when undercarriage handle is placed in receiving/releasing undercarriage, order simulation undercarriage
Position sensor up to puts down or is lowered into entirely the upper process of full receipts entirely from full receipts, checks during each step, undercarriage control
Whether the driving order of magnetic valve is consistent with design requirement.
3. configure No. 2 bus transceivers of control unit and be in disabled status, now RS422 buses distributor passes through information
No. 2 bus datas of control unit of processor simulation, operate folding and unfolding joystick, when verifying that single control unit works, can
The normal folding and unfolding work of landing system is completed, as shown in Figure 4.
Normally closed switch controls two working conditions of equipment RS422 buses.
Two RS422 bus transceivers are in parallel with equipment room communication bus, can receive and process the total of two equipment output
Line number evidence.
When normally closed switch is closed, two RS422 bus transceivers only gather two bus datas of equipment output, by letter
Breath processor is exported to visualization device.
When normally closed switch disconnects, two RS422 bus transceivers receive two bus datas of equipment output, by information
Processor is reconstructed to landing gear position sensor or control unit state parameter, and exports to corresponding another equipment.
Claims (3)
1. a kind of Aircraft landing gear system RS422 bus data verification methods, using two RS422 bus transceivers, at two
A normally closed switch is connect on bus communication circuit between RS422 bus transceivers；Two RS422 bus transceivers are and information
Processor is connected；Bus communication circuit two ends connect No. 1 control unit and No. 2 control units respectively；No. 1 control unit and No. 2 controls
Unit processed is connected with landing gear position sensor；The method includes：
The sampling period of message handler configuration RS422 bus transceivers is 10ms, and baud rate is 9600, counts a sampling week
The interim byte number for retrieving, effective word joint number is less than 9 bytes, then meet transmission demand；More than 9 bytes, then baud rate is configured
It is 19200, the byte number retrieved in one sampling period of statistics, effective word joint number is less than 21 bytes, then meet transmission demand；
Message handler changes the position sensing that No. 1 control unit or No. 2 control units are gathered by RS422 bus transceivers
Device signal, is modified signal transmission to No. 2 control units, by No. 2 control units by RS422 buses by No. 1 control unit
The different parameters for being modified signal transmission to No. 1 control unit, simulating landing gear position sensor, when No. 1 control unit inspection
Measure position sensor display undercarriage to receive entirely, No. 2 control unit position sensors are modified during to complete putting down, control unit
Report failure；When No. 1 control unit detects position sensor display undercarriage just in folding and unfolding centre position, No. 2 control unit inspections
Measure position sensor display undercarriage in place when, control unit drive undercarriage start instruction stop and report failure；
No. 2 bus transceivers of control unit of configuration are in disabled status, and now RS422 bus transceivers pass through message handler
No. 2 bus datas of control unit of simulation, acquiescence undercarriage is in down state, operates folding and unfolding joystick to retracted position,
Message handler is simulated nose-gear bottom lock sensor and is unlocked successively by RS422 buses, main landing gear bottom lock sensor
Unlock, the upper lock sensor of nose-gear is locked, and the upper lock sensor of main landing gear is locked, in the process No. 2 control units
Magnetic valve output interface drives nose-gear down lock unlocking valve, main landing gear down lock unlocking valve, in nose-gear receipts successively
Valve, main landing gear receives upper valve conducting, then meet and receive upper demand；
To extended position, message handler simulates nose-gear uplock to operation folding and unfolding joystick successively by RS422 buses
Sensor is unlocked, and the upper lock sensor of main landing gear is unlocked, and nose-gear bottom lock sensor is locked, and main landing gear down lock is passed
Sensor is locked, and No. 2 control unit magnetic valve output interfaces drive nose-gear uplock unlocking valve successively in the process, lead
Fall frame uplock unlocking valve, and nose-gear puts down valve, and main landing gear puts down valve conducting, then meet and put down demand.
2. Aircraft landing gear system RS422 bus data verification methods according to claim 1, it is characterised in that described
Message handler is connected with visualization device.
3. a kind of Aircraft landing gear system RS422 bus datas verify device, it is characterised in that including connecting with bus communication circuit
Two 422 bus transceivers for connecing, are connected to one and normally closed open on the bus communication circuit between two RS422 bus transceivers
Close；Bus communication circuit two ends connect No. 1 control unit and No. 2 control units respectively；No. 1 control unit and No. 2 control units are equal
It is connected with landing gear position sensor；Described information processor is connected with visualization device.
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| CN201611014053.4A CN106742048B (en) | 2016-11-18 | 2016-11-18 | A kind of Aircraft landing gear system RS422 bus data verification method and device |
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| CN201611014053.4A CN106742048B (en) | 2016-11-18 | 2016-11-18 | A kind of Aircraft landing gear system RS422 bus data verification method and device |
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| CN106742048B CN106742048B (en) | 2019-02-15 |
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Cited By (6)
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| CN109561007A (en) * | 2018-11-16 | 2019-04-02 | 安徽华明航空电子系统有限公司 | A kind of navigation aircraft avionics system design method based on FlexRay bus |
| CN110304268A (en) * | 2019-06-20 | 2019-10-08 | 成都飞机工业（集团）有限责任公司 | A kind of general assembly test method of aircraft system |
| CN110963074A (en) * | 2019-12-25 | 2020-04-07 | 中航贵州飞机有限责任公司 | Unmanned aerial vehicle undercarriage signal simulation system |
| CN111143266A (en) * | 2019-12-24 | 2020-05-12 | 成都国翼电子技术有限公司 | RS422 bus multi-master device link control system |
| CN111385178A (en) * | 2019-12-24 | 2020-07-07 | 成都国翼电子技术有限公司 | RS422 bus link monitoring and network failure protection system |
| CN112532497A (en) * | 2020-12-04 | 2021-03-19 | 中国航空工业集团公司成都飞机设计研究所 | CAN bus framework of aircraft landing gear system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109561007A (en) * | 2018-11-16 | 2019-04-02 | 安徽华明航空电子系统有限公司 | A kind of navigation aircraft avionics system design method based on FlexRay bus |
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| CN106742048B (en) | 2019-02-15 |
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