CN109987250A - A kind of aircraft movable wing adjustment detection system and adjustment detection method - Google Patents
A kind of aircraft movable wing adjustment detection system and adjustment detection method Download PDFInfo
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- CN109987250A CN109987250A CN201910270249.7A CN201910270249A CN109987250A CN 109987250 A CN109987250 A CN 109987250A CN 201910270249 A CN201910270249 A CN 201910270249A CN 109987250 A CN109987250 A CN 109987250A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
This application discloses a kind of aircraft movable wing adjustment detection system and adjustment detection methods, including signal process box, board subrack, Comprehensive control computer, programmable power supply, display and mating cable, signal process box carries out the metering of fault location and aircraft movable wing detection detection system, mating cable connection signal conditioning case and wing, each actuator on empennage, rudder face position sensor, board subrack provides drive ram stretching motion after required excited signal improves work order, Comprehensive control computer sends operator's instruction by human-computer interaction interface, control movable wing movement, and the motion state of aerofoil is fed back into software interface, complete aileron, spoiler, aileron position sensor, elevator, rudder, the adjustment and detection of elevator position sensor.
Description
Technical field
It is specifically a kind of for movable wing in aircraft components assembling stage the present invention relates to aircraft movable wing measuring technology
The adjustment detection system and method in face.
Background technique
The movable wing of aircraft refers to wing, on empennage mainly can include elevator, pair by the aerofoil of manipulation and control
The wing, rudder, spoiler etc., fly-by-wire flight control system by the deflection of each movable wing of operating aircraft realize aspect,
The control in course, the variation of small parameter can impact flight attitude on aerofoil, therefore movable wing is relationship aircraft
The important component of flight safety.
It will form certain cumulative errors due to factors such as manufacture, assembly technologies in the production phase of aircraft, if not flying
The adjustment that the machine fabrication stage carries out movable wing detects work, then it cannot be guaranteed that the energization inspection result in general assembly stage complies fully with
Technical requirements in aircraft layout about aerofoil indices.Although certain aircrafts use in the design of flight control system
Plane airfoil automatic zero set mechanism does not have to adjust movable wing after the completion of portion's dress work, directly passes through in the general assembly stage and flies control system
System carries out aerofoil automatic zero set to offset part installation error, if but accumulative installation error it is excessive, exceed aerofoil automatic zero set model
It encloses, the automatic zero set mechanism of flight control system then cannot achieve the zero-bit adjustment of rudder face, also not can guarantee the pole that aerofoil can reach
Limit deflection angle.
Therefore, in the component assembling stage of aircraft wing, empennage, the deflection characteristic of movable wing need to be detected, is surveyed
Examination project include the neutral position of rudder face, the limit deflection angle of rudder face, deflection process uniformity, pass through " performance test-peace
Adjustment is whole-performance test " this process that iterates, and continuous adjustment assembly size reduces cumulative errors, until aerofoil deflects
Performance reaches within the scope of technical indicator allowable error, just can component be delivered to next stage of Aircraft Production.
There are mainly two types of method, methods one are as follows: in aircraft wing, empennage for the existing adjustment detection for aircraft movable wing
Portion dress the stage carry out movable wing adjustment detection.Due to portion dress the stage be only mounted with the wing of aircraft, empennage movable wing,
Correlation computer class finished product is not installed in the actuator and rudder face position sensor, flight control system of each movable wing, Wu Fali
Electricity consumption transmission control molding state carries out movable wing adjustment detection, actuator can only be in damping operation mode, by manually loading
The mode of external force carries out the deflection of rudder face, and this method excessively relies on manual operation experience, if manipulating, external force is excessive to will cause activity
The damage of aerofoil appearance increases aircraft manufacturing cost.Method two are as follows: wing, empennage portion, which are installed into, is directly entered aircraft general assembly rank
Section, it is whole after the installation is completed to flight control system finished product and airborne cable, movable wing adjustment inspection is carried out using Flying by wire mode
Survey, if movable wing adjustment detection it is unqualified, need to the portion of being back to dress the stage ressemble after carry out general assembly test, installation step again
Counteroffensive will seriously affect the manufacturing progress of aircraft.
Summary of the invention
Aiming at the problems existing in the prior art, the object of the present invention is to provide a kind of adjustment of aircraft movable wing to examine
Examining system.
A kind of aircraft movable wing adjusts detection system, including signal process box, board subrack, Comprehensive control computer,
Receptacle array is distributed in programmable power supply, display and mating cable, signal process box rear panel, passes through mating cable and each aerofoil
Actuator, board subrack, carries out interconnection of signals and adaptation, each socket between Comprehensive control computer at rudder face position sensor
It is both designed as error protection socket and makes silk-screen mark, disconnection block array, signal condition is distributed in the front panel of signal process box
It is equipped with core wire beam inside case, the signal of rear panel is introduced on the disconnection block of front panel and carries out fault location and aircraft movable wing
Face adjusts the metering of detection system, aileron actuator, spoiler actuator, aileron position sensing on mating cable connection wing
Device completes the adjustment and detection of aileron, spoiler, aileron position sensor, elevator actuator on mating cable connection empennage,
Rudder actuator, elevator position sensor complete the adjustment and detection of elevator, rudder, elevator position sensor；
Actuator of the board subrack by excitation plate, servo amplification board, signal demodulation board group at, excitation plate to tested aerofoil, rudder face position
Sensor provides required excited signal, drive ram stretching motion after servo amplification board improves work order, signal solution
AC signal is demodulated into after direct current signal and constitutes closed-loop control with command signal synthesis by tuned plate；Comprehensive control computer operation has
Test software is matched with display, and is configured with remote communications port, and test software includes that aerofoil adjusts detection module, rudder
Face position sensor detection module, communication module, aerofoil adjust detection module and are referred to by human-computer interaction interface transmission operator
It enables, control movable wing movement, and the motion state of aerofoil is fed back into software interface, complete the adjustment inspection of aircraft movable wing
Experiment work is surveyed, rudder face position sensor detection module sends the electrical instruction of operator, while acquiring and showing the sensing
Output signal when device moves, completes the detection experiment work of rudder face position sensor, and communication module realizes aircraft movable wing
The communication between detection system and production scene hydraulic oil source system, drift angle detection system is adjusted, is being tried convenient for operator
Overall arrangement and security protection in testing；Programmable power supply is opened or closed by test software control, for respectively surveying to board subrack
Test plate (panel) card and signal process box provide working power.
Test software design has separation test, limit protection, power-off preventing mechanism, and separation testing mechanism is to be only capable of every time
The test for carrying out the single actuator of aerofoil to be measured, by aerofoil to be measured, remaining actuator is placed in the servo-actuated state of damping, solves activity
Power dispute problem when aerofoil adjustment detection；Limit protection mechanism is to acquire the rudder face position ginseng of external drift angle detection system simultaneously
The rudder face location parameter of number, this patent, is comprehensively compared, and when any value arrival aerofoil tilt limit, then sends stopping
Instruction, stops the movement of the movable wing；If operational order is unable to control aerofoil and stops in movable wing adjustment detection process,
And aerofoil have the tendency that continue to extreme position deflect, using power-off preventing mechanism forcibly close power supply, prevent movable wing by
Damage.
The method for carrying out the deflection detection of aircraft movable wing using the system, comprising the following steps:
Step 1: after aircraft wing, the stage assembly of empennage portion dress, mating cable connection signal being improved into case and aileron
Actuator, spoiler actuator, elevator actuator, rudder actuator, aileron position sensor, elevator position sensing
Device, by cable connection all round computer and hydraulic oil source system, drift angle detection system；
Step 2: by fluid pressure line connection hydraulic oil source system and aileron actuator, spoiler actuator, elevator actuation
Device, rudder actuator；
Step 3: aircraft movable wing adjusts detection system, the power-up initializing of drift angle detection system normally, opens hydraulic oil
Source system is simultaneously adjusted to operating pressure, and hydraulic oil source system, drift angle detection system and aircraft movable wing adjustment detection system are logical
News are normal；
Step 4: the single actuator of movable wing to be detected is selected in test software, which is powered, remaining work
Dynamic device is in damping state, and rudder face position sensor is powered；
Step 5: sending movable wing deflection command, read movable wing actuator, rudder face position sensor running parameter
State is simultaneously parsed into physical quantity meaning；
Step 6: repeating step 5, send the deflection command of movable wing different location；
Step 7: the instruction of movable wing neutral position is sent, to aerofoil Hui Zhonghou, actuator power-off, rudder face position sensing
Device power-off；
Step 8: whether the technical indicator that judgment step 5,6 is tested meets design requirement, if not meeting design requirement, closes
Hydraulic oil source system, aircraft movable wing adjustment detection system and drift angle detection system are closed, ressembles and adjusts the aerofoil or work
Dynamic device, repeats step 3,4,5,6,7,8 after adjustment, until step 5,6 measuring technology indexs meet design requirement, if step 5,
The technical indicator of 6 tests meets design requirement, then carries out the test of step 9；
Step 9: choosing whether to continue the test of remaining actuator of movable wing to be detected, if continued, weigh
Otherwise multiple step 4,5,6,7,8 close hydraulic oil source system, aircraft movable wing adjustment detection system and drift angle detection system,
Detection terminates.
The application is a kind of movable wing adjustment detection system used in the dress stage in aircraft portion, the beneficial effect is that:
(1) it solves the problems, such as to detect by artificial means in the prior art, improves the experimental condition of plane airfoil, contract
In the short aircraft assembling manufacturing period, it ensure that Aircraft Production progress；
(2) degree of integration is high, is the integration test for integrating the detection of aircraft movable wing, the detection of rudder face position sensor
System, high degree of automation are easy to operate easy-to-use；
(3) possess perfect movable wing driving safety protecting mechanism, test is safe and reliable.
Detailed description of the invention
Fig. 1 aircraft movable wing adjusts detection system composition figure
Fig. 2 wing movable wing adjustment detection embodiment schematic diagram
Fig. 3 empennage movable wing adjustment detection embodiment schematic diagram
In figure number explanation: 1 aircraft movable wing adjust detection system, 2 displays, 3 signal process box, 4 board subracks,
5 Comprehensive control computers, 6 programmable power supplys, 7 cables, 8 mating cables, 9, fluid pressure line, 10 ailerons, 11 spoilers, 12 liftings
Rudder, 13 rudders, 14 wings, 15 empennages.
Specific embodiment
As shown in Figure 1-3, aircraft movable wing adjusts detection system 1, include signal process box 3, board subrack 4, synthesis
Control computer 5, programmable power supply 6, display 2 and mating cable 8.
Receptacle array is distributed in the rear panel of signal process box 3, passes through mating cable 8 and each aerofoil actuator, rudder face position
It sets sensor, board subrack 4, carry out interconnection of signals between Comprehensive control computer 5 and adaptation, each socket are both designed as anti-difference
Misplug seat simultaneously makes silk-screen mark, and disconnection block array is distributed in the front panel of signal process box 3, is equipped with core inside signal process box
The signal of rear panel is introduced on the disconnection block of front panel convenient for fault location and aircraft movable wing adjustment detection system by harness
The metering of system 1.Mating cable 8 is connected into aileron actuator, spoiler actuator, aileron position sensor on wing 14, it can be complete
At the adjustment and detection of aileron 10, spoiler 11, aileron position sensor.Mating cable 8 is connected elevator on empennage 15 to make
Dynamic device, rudder actuator, elevator position sensor, achievable elevator 12, rudder 13, elevator position sensor
Adjustment and detection.
Board subrack 4 by excitation plate, servo amplification board, signal demodulation board group at.Actuator from excitation plate to tested aerofoil,
Rudder face position sensor provides required excited signal, the flexible fortune of drive ram after servo amplification board improves work order
Dynamic, AC signal is demodulated into after direct current signal and constitutes closed-loop control with command signal synthesis by signal solution tuned plate.
The operation of Comprehensive control computer 5 has test software to match with display 2, and is configured with remote communications port.
The test software uses modularized design, includes aerofoil adjustment detection module, rudder face position sensor detection module, communication
Module.Aerofoil adjusts detection module and sends operator's instruction by human-computer interaction interface, and control movable wing moves, and by the wing
The motion state in face feeds back to software interface, and the adjustment for completing aircraft movable wing detects experiment work；Rudder face position sensor
Detection module sends the electrical instruction of operator, while acquiring and showing the output signal when sensor moves, and completes rudder
The detection experiment work of face position sensor；Communication module realizes aircraft movable wing adjustment detection system 1 and production scene liquid
The communication between oil supply system, drift angle detection system is pressed, convenient for the overall arrangement and security protection of operator in test.
Test software design has separation test, limit protection, power-off preventing mechanism.Separation testing mechanism is to be only capable of every time
The test for carrying out the single actuator of aerofoil to be measured, by aerofoil to be measured, remaining actuator is placed in the servo-actuated state of damping, solves activity
Power dispute problem when aerofoil adjustment detection；Limit protection mechanism be the rudder face position for acquiring external drift angle detection system simultaneously,
The rudder face location parameter of this patent, is comprehensively compared, and when any value arrival aerofoil tilt limit, is then sent stopping and is referred to
It enables, stops the movement of the movable wing；If operational order is unable to control aerofoil and stops in movable wing adjustment detection process, and
Aerofoil have the tendency that continue to extreme position deflect, can be used power-off preventing mechanism forcibly close power supply, prevent movable wing by
Damage.
Programmable power supply 6 is opened or closed by test software control, is used for each test board of board subrack 4 and signal condition
Case 3 provides working power.
The method for carrying out aircraft movable wing detection with the system, including following testing procedure:
Step 1: after 15 aircraft wing 14, empennage dress stage assembly, mating 8 connection signal of cable being improved into case 3
With aileron actuator, spoiler actuator, elevator actuator, rudder actuator, aileron position sensor, elevator position
Cable 7 is connected all round computer 5 and hydraulic oil source system, drift angle detection system by sensor；
Step 2: fluid pressure line 9 is connected into hydraulic oil source system and aileron actuator, spoiler actuator, elevator actuation
Device, rudder actuator；
Step 3: aircraft movable wing adjusts detection system 1, the power-up initializing of drift angle detection system normally, opens hydraulic oil
Source system is simultaneously adjusted to operating pressure, and hydraulic oil source system, drift angle detection system and aircraft movable wing adjustment detection system 1 are logical
News are normal；
Step 4: the single actuator of movable wing to be detected is selected in test software, which is powered, remaining work
Dynamic device is in damping state, and rudder face position sensor is powered；
Step 5: sending movable wing deflection command, read movable wing actuator, rudder face position sensor running parameter
State is simultaneously parsed into physical quantity meaning；
Step 6: repeating step 5, send the deflection command of movable wing different location；
Step 7: the instruction of movable wing neutral position is sent, to aerofoil Hui Zhonghou, actuator power-off, rudder face position sensing
Device power-off；
Step 8: whether the technical indicator that judgment step 5,6 is tested meets design requirement, if not meeting design requirement, closes
Hydraulic oil source system, aircraft movable wing adjustment detection system and drift angle detection system are closed, ressembles and adjusts the aerofoil or work
Dynamic device, repeats step 3,4,5,6,7,8 after adjustment, until step 5,6 measuring technology indexs meet design requirement, if step 5,
The technical indicator of 6 tests meets design requirement, then carries out the test of step 9；
Step 9: choosing whether to continue the test of remaining actuator of movable wing to be detected, if continued, weigh
Otherwise multiple step 4,5,6,7,8 close hydraulic oil source system, aircraft movable wing adjustment detection system 1 and drift angle detection system,
Detection terminates.
Claims (3)
1. a kind of aircraft movable wing adjusts detection system, including signal process box, board subrack, Comprehensive control computer, journey
Control power supply, display and mating cable, it is characterised in that receptacle array is distributed in the signal process box rear panel, by matching
Cover cable and each aerofoil actuator, rudder face position sensor, board subrack, carry out between Comprehensive control computer interconnection of signals and
Adaptation, each socket are both designed as error protection socket and make silk-screen mark, and disconnection block is distributed in the front panel of signal process box
Array, signal process box inside are equipped with core wire beam, and the signal of rear panel is introduced to progress failure on the disconnection block of front panel and is determined
The metering of position and aircraft movable wing detection detection system, aileron actuator on mating cable connection wing, spoiler actuator,
Aileron position sensor, completes the adjustment and detection of aileron, spoiler, aileron position sensor, and mating cable connects on empennage
Elevator actuator, rudder actuator, elevator position sensor complete elevator, rudder, elevator position sensor
Adjustment and detection；The board subrack is by excitation plate, servo amplification board, signal demodulation board group at, excitation plate to the tested wing
The actuator in face, rudder face position sensor provide required excited signal, and servo amplification board acts work order conditioning rear-guard
AC signal is demodulated into after direct current signal and constitutes closed-loop control with command signal synthesis by dynamic device stretching motion, signal solution tuned plate；
The Comprehensive control computer operation has test software to match with display, and is configured with remote communications port, test
Software includes that aerofoil adjusts detection module, rudder face position sensor detection module, communication module, and aerofoil adjustment detection module passes through
Human-computer interaction interface sends operator's instruction, control movable wing movement, and the motion state of aerofoil is fed back to software circle
Face, the adjustment for completing aircraft movable wing detect experiment work, and rudder face position sensor detection module sends the logical of operator
Electricity instruction, while acquiring and showing the output signal when sensor moves, work is tested in the detection for completing rudder face position sensor
Make, communication module realizes aircraft movable wing adjustment detection system and production scene hydraulic oil source system, drift angle detection system
Between communication, convenient for the overall arrangement and security protection of operator in test；The programmable power supply is by test software
Control opens or closes, for providing working power to each test board of board subrack and signal process box.
2. a kind of aircraft movable wing described in claim 1 according to adjusts detection system, spy is the survey
Examination software design has separation test, limit protection, power-off preventing mechanism, and separation testing mechanism is only to can be carried out the wing to be measured every time
The test of the single actuator in face, by aerofoil to be measured, remaining actuator is placed in the servo-actuated state of damping, solves movable wing adjustment inspection
Power dispute problem when survey；Limit protection mechanism is the rudder face location parameter for acquiring external drift angle detection system simultaneously, is carried out comprehensive
Composition and division in a proportion compared with, when any value reach aerofoil tilt limit, then send halt instruction, stop the movement of the movable wing；In work
If operational order is unable to control aerofoil stopping in dynamic aerofoil adjustment detection process, and aerofoil has continuation to become to what extreme position deflected
Gesture forcibly closes power supply using power-off preventing mechanism, prevents movable wing impaired.
3. a kind of aircraft movable wing adjusts detection method, it is characterised in that the following steps are included:
Step 1: after aircraft wing, the stage assembly of empennage portion dress, by mating cable connection signal conditioning case and aileron actuation
Device, spoiler actuator, elevator actuator, rudder actuator, aileron position sensor, elevator position sensor, will
Cable connects all round computer and hydraulic oil source system, drift angle detection system；
Step 2: by fluid pressure line connection hydraulic oil source system and aileron actuator, spoiler actuator, elevator actuator, side
To rudder actuator；
Step 3: aircraft movable wing adjusts detection system, the power-up initializing of drift angle detection system normally, opens hydraulic oil source system
It unites and adjusts to operating pressure, hydraulic oil source system, drift angle detection system and the communication of aircraft movable wing adjustment detection system are just
Often；
Step 4: the single actuator of movable wing to be detected is selected in test software, which is powered, remaining actuator
In damping state, rudder face position sensor is powered；
Step 5: sending movable wing deflection command, read movable wing actuator, rudder face position sensor running parameter state
And it is parsed into physical quantity meaning；
Step 6: repeating step 5, send the deflection command of movable wing different location；
Step 7: sending the instruction of movable wing neutral position, to aerofoil Hui Zhonghou, actuator power-off, rudder face position sensor is disconnected
Electricity；
Step 8: whether the technical indicator that judgment step 5,6 is tested meets design requirement, if not meeting design requirement, closes liquid
Oil supply system, aircraft movable wing adjustment detection system and drift angle detection system are pressed, ressembles and adjusts the aerofoil or actuator,
Step 3,4,5,6,7,8 are repeated after adjustment, until step 5,6 measuring technology indexs meet design requirement, if step 5,6 tests
Technical indicator meet design requirement, then carry out the test of step 9；
Step 9: choosing whether to continue the test of remaining actuator of movable wing to be detected, if continued, repeat to walk
Rapid 4, otherwise hydraulic oil source system, aircraft movable wing adjustment detection system and drift angle detection system, detection are closed in 5,6,7,8
Terminate.
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| CN111017195A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | System and method for verifying non-instruction motion protection of flap |
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| CN114872927A (en) * | 2022-05-27 | 2022-08-09 | 浙江大学 | Airplane movable wing surface detection method and system based on wireless sensor |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111017195A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | System and method for verifying non-instruction motion protection of flap |
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| CN113968358A (en) * | 2021-10-28 | 2022-01-25 | 西安羚控电子科技有限公司 | Operation inspection method and system of fixed-wing unmanned aerial vehicle |
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| CN114872927A (en) * | 2022-05-27 | 2022-08-09 | 浙江大学 | Airplane movable wing surface detection method and system based on wireless sensor |
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