CN107271161A - A kind of aircraft door durability test device - Google Patents
A kind of aircraft door durability test device Download PDFInfo
- Publication number
- CN107271161A CN107271161A CN201710407971.1A CN201710407971A CN107271161A CN 107271161 A CN107271161 A CN 107271161A CN 201710407971 A CN201710407971 A CN 201710407971A CN 107271161 A CN107271161 A CN 107271161A
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- China
- Prior art keywords
- aircraft door
- stepper motor
- door
- aircraft
- control
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
Abstract
The present invention provides a kind of aircraft door durability test device, including：Load test system is coordinated in microcomputer control, and it carries out whole-process control and tracking to experiment；Stepper motor driver, it is received controls to coordinate the instruction of load test system from the microcomputer；Stepper motor, it is driven by the stepper motor driver, to drive the aircraft door according to predetermined speed and angular movement, realizes the switch motion of the aircraft door；Angular displacement sensor, its kinematic parameter for being used to gather the aircraft door is simultaneously provided to microcomputer control coordination load test system, the microcomputer control coordinates load test system and controls the kinematic parameter for coordinating to set in load test system to be compared with the microcomputer kinematic parameter collected, to determine whether to control the aircraft door to continue to move；And test console, it is provided with the protection button for being used for stopping experiment.
Description
Technical field
The present invention relates to aircraft door endurancing, and in particular to a kind of aircraft door durability test device.
Background technology
Civil aircraft door design is difficult point and emphasis in civil aircraft structure, its reliability and anallobar hatch door it is airtight
Performance directly influences the safety of passenger and crew, and influences the operability of ground crew, is aiMonhiness authority's focal point
One of.
Aircraft door endurancing be inspection and test hatch door mechanism kinematic during wear and tear on motion influence
Important method, is also the important channel that foundation is provided for door design development.Can hatch door mechanism normally transport within the design cycle
Dynamic completion and the Flight Safety for directly affecting aerial mission.Analysed in depth by the type testing data to hatch door,
It can improve and optimization design, the reliability of examination key mechanism and mechanism, so as to design safe and reliable aircraft door, protect
Demonstrate,prove Flight Safety.
China starts late in aircraft door endurancing field, especially in Import computer switch testing field, base
Originally blank is belonged to.Because aircraft door unsealing mechanism is complicated, it is related to interior receipts, deflected and several big steps of turning up, and enabling track is answered
Miscellaneous, parameter fitting difficulty is high.Once there is the trial using artificial repeat switch door, but because testing itself cycle length (240,000 times), people
Work unlatching is stablized, and poor, introducing uncertain factor is more, it is difficult to long lasting for progress.The use of machinery equipment switch hatch door is the experiment
The key link that success is carried out.
The content of the invention
In order to solve the above-mentioned problems in the prior art, it is an object of the invention to provide a kind of aircraft door is durable
Property experimental rig, come realize automation open and close hatch door, mitigate human users' burden, meet experimental test requirement.
According to an aspect of the present invention there is provided a kind of aircraft door durability test device, aircraft door includes passing through
Arm pivot post is fixed on the handle of the side of the aircraft door, and the opposite side of the aircraft door is rotatable by linkage
Ground is fixed to hatch door framework, and the linkage includes being installed to the hinge rotating shaft of the aircraft door and is installed to the hatch door
The hinge rotating shaft of framework, the aircraft door durability test device includes：
Load test system is coordinated in microcomputer control, and it carries out whole-process control and tracking to experiment；
Stepper motor driver, it is received controls to coordinate the instruction of load test system from the microcomputer；
Stepper motor, it is driven by the stepper motor driver, to drive the aircraft door according to predetermined speed
And angular movement, realize the switch motion of the aircraft door；
Angular displacement sensor, its kinematic parameter for being used to gather the aircraft door is simultaneously provided to microcomputer control coordination
Load test system, microcomputer control coordinate kinematic parameter that load test system collects the angular displacement sensor with
The kinematic parameter that setting in load test system is coordinated in the microcomputer control is compared, to determine whether to control the aircraft cabin
Door continues to move；And
Test console, it is provided with the protection button for being used for stopping experiment.
Wherein, the aircraft door durability test device also includes Fu Men mechanisms, and the Fu Men mechanisms are arranged on described
The aircraft door is driven to move below aircraft door.
Wherein, the Fu Men mechanisms include bent frame, the first gyroaxis being arranged on the bent frame, the second gyroaxis and the
Three gyroaxises, the stepper motor include be arranged on the first gyroaxis the first stepper motor, be arranged on the second gyroaxis
The second stepper motor and the 3rd stepper motor that is arranged on the 3rd gyroaxis, the hand of the first gyroaxis and the aircraft door
Handle rotating shaft is coaxially arranged, and hinge rotating shaft of second gyroaxis with being installed to the aircraft door is coaxially arranged, the 3rd gyroaxis with
The hinge rotating shaft for being installed to the hatch door framework is coaxially arranged.
Wherein, load test system is coordinated in the microcomputer control includes control software, control computer, driving stepper motor card
With A/D collection plates；
The control software is used to carry out position clearing to the Fu Men mechanisms；
The control computer sends instruction to the driving stepper motor card, and the driving stepper motor card is by control parameter
Pulse be sent to the stepper motor driver, to drive the stepper motor to be rotated according to control parameter, so as to drive institute
State aircraft door motion；And
The kinematic parameter of the aircraft door is supplied to A/D collection plates, the A/D collection plates by the angular displacement sensor
Digital data transmission is converted the signal into the control computer.
Wherein, the test console is additionally provided with limit switch, is transfinited when aircraft door motion and touches described spacing
Switch, the test console is automatically stopped experiment.
In order to simulate the switch operation of aircraft door, while extra load can not be brought to aircraft door again, design one
Tao Fumen mechanisms are arranged on the underface of aircraft door testpieces, and the facility of operating aircraft hatch door motion is all fixed on secondary door machine
On structure, the operating of aircraft door is driven by manipulating Fu Men mechanisms, the action of switch aircraft door is realized.
Set three gyroaxises in Fu Men mechanisms, these three gyroaxises respectively with aircraft door arm pivot post and two switch gates
Hinge rotating shaft is coaxial, and a stepper motor is laid respectively at three gyroaxises of Fu Men mechanisms, the stepping electricity controlled by computer
Machine drives aircraft door handle and switch door hinge motion, so as to realize the switch motion of aircraft door.
Brief description of the drawings
The further feature and advantage of the present invention will be more preferable by the preferred embodiment being described in detail below in conjunction with accompanying drawing
Ground understanding, wherein：
Fig. 1 shows the operating principle figure of the aircraft door durability test device according to the present invention.
Fig. 2 shows the schematic diagram that initial position is according to the aircraft door durability test device of the present invention；
Fig. 3 is shown according to the aircraft door durability test device of present invention schematic diagram in an intermediate position；And
Fig. 4 shows the schematic diagram that full open position is according to the aircraft door durability test device of the present invention.
Embodiment
In the specific descriptions of following preferred embodiment, by the accompanying drawing with reference to appended by constituting a present invention part.Institute
Attached accompanying drawing, which has been illustrated by way of example, can realize specific embodiment.The embodiment of example is not intended as
Limit is according to all embodiments of the invention.It is appreciated that without departing from the scope of the present invention, it is possible to use other
Embodiment, can also carry out structural or logicality modification.
As shown in fig. 1, microcomputer control is mainly included according to the aircraft door durability test device of the present invention to coordinate to add
Carry pilot system 10, stepper motor driver 20, stepper motor 30, angular displacement sensor 40 and test console (not shown).
Load test system 10 is coordinated in microcomputer control includes control software, control computer 11, the and of driving stepper motor card 12
A/D collection plates 13, it carries out whole-process control and tracking to experiment, and work order is sent to drive system, gathers feedback signal, association
Adjust each Channel Synchronous to run, record test number (TN).
Stepper motor 20 and stepper motor driver 30 are experiment executing agency, and they receive microcomputer control and coordinate loading examination
The signal that check system 10 is sent, driving aircraft door 50 is according to predetermined speed and angular movement.
Angular displacement sensor 40 gathers the switch angle and running speed of aircraft door 50, and gives microcomputer control by signal
Coordinate load test system 10, the kinematic parameter that load test system 10 collects angular displacement sensor 40 is coordinated in microcomputer control
The kinematic parameter for coordinating setting in load test system 10 is controlled to be compared with microcomputer, to determine whether to control aircraft door 50
Continue to move.
Test console major function is that in case of emergency, testing crew presses " protection " button and stops experiment, also
Have, testpieces moves the shake-up limit switch that transfinites, test console is automatically stopped experiment.
Hatch door endurancing control principle drawing is shown in Fig. 1, by control computer 11, driving stepper motor card 12, stepper motor
Driver 20, stepper motor 30, angular displacement sensor 40 and A/D collection plates 13 etc. constitute closed-loop control system.During experiment, control
Computer 11 sends instruction to driving stepper motor card 12, and driving stepper motor card 12 sends a series of carrying control parameters (such as：Side
To, speed and stroke etc.) pulse to stepper motor driver 20, the Driving Stepping Motor 30 of stepper motor driver 20 is according to control
Parameter rotation processed, drives aircraft door handle and secondary door mechanism kinematic, so as to realize the motion of aircraft door.In Fu Men mechanisms and
Kinematic parameter at angular displacement sensor 40, collection Fu Men mechanisms and aircraft door handle is installed at aircraft door handle to be supplied to
A/D collection plates 13, A/D collection plates 13 convert the signal into digital data transmission and give control computer 11, and control computer 11 will be gathered
To feedback signal compared with output signal, if the difference drawn carries out next step behaviour into error band allowed band
Make；If difference is not entered into the range of error band, control computer 11 sends instruction again, and control system continues to move, Zhi Daoman
Untill foot is required, next step operation is then carried out.
As shown in Fig. 2 to Fig. 4, aircraft door durability test device also includes Fu Men mechanisms 60, and Fu Men mechanisms 60 are pacified
Aircraft door 50 is driven to move mounted in the lower section of aircraft door 50.Fu Men mechanisms 60 include bent frame 61, are arranged on bent frame 61
The first gyroaxis 62, the second gyroaxis 63 and the 3rd gyroaxis 64.Stepper motor 30 includes being arranged on the first gyroaxis 62
The first stepper motor 31, the second stepper motor 32 for being arranged on the second gyroaxis 63 and be arranged on the 3rd gyroaxis 64
3rd stepper motor 33.Aircraft door 50 includes the handle 51 that the side of aircraft door 50 is fixed on by arm pivot post, aircraft
The opposite side of hatch door 50 is rotatably fixed to hatch door framework 70 by linkage 80, and linkage 80 includes being installed to aircraft
The hinge rotating shaft 81 of hatch door 50 and the hinge rotating shaft 82 for being installed to hatch door framework 70.The hand of first gyroaxis 62 and aircraft door 50
Handle rotating shaft is coaxially arranged, and hinge rotating shaft of second gyroaxis 63 with being installed to aircraft door 50 is coaxially arranged, the 3rd gyroaxis 64
It is coaxially arranged with the hinge rotating shaft that is installed to hatch door framework 70.
Aircraft door 50 first rotates clockwise the lock-out state that handle 51 releases aircraft door 50 when opening, and now, flies
Cabin door 50 is overall motionless, and the also transfixion of Fu Men mechanisms 60, only handle 51 drives rotation by the first stepper motor 31.Unblock
After completion, handle 51 is rotated further to about 126 °, and the aircraft door operating mechanism interlocked during this with handle 51, which drives, to fly
Cabin door 50 is inwardly received, while Handle axis overhead cam drives and received above and below door in leaf hinge and latch hook switching mechanism is by latch hook on door
Open, handle 51 also receives inwards with aircraft door 50, the first stepper motor 31 being rotated further with fixed handle 51 also should be with
Inside receipts, be so just avoided that the first stepper motor 31 being fixed on the bent frame of Fu Men mechanisms is produced to handle extra negative
The second stepper motor 32 and the 3rd stepper motor that load test system control Fu Men mechanisms are rotated are coordinated in lotus, at this moment microcomputer control
33 start running, manipulate Fu Men mechanisms 60 and aircraft door 50 synchronously rotate in same direction, the first stepper motor of drive 31 and handle 51
It is servo-actuated.In motion process, handle 51 can be rotated further.
After handle 51 is rotated in place, aircraft door 50 moves to estimating position, the secondary door that adjustment is synchronized with the movement with hatch door
Controlling organization pins Fu Men mechanisms angles and positions, and switch gate executing agency starts, the rotation of control Fu Men mechanisms, Fu Men mechanisms with
Aircraft door bindiny mechanism drives aircraft door together to be rotated around its installation axle, realizes the door opening action of aircraft door.
The closing process of aircraft door is with door opening process completely on the contrary, control principle is identical.
The technical effects of the invention are that：
1st, in order to simulate the switch operation of aircraft door, while extra load can not be brought to aircraft door again, design
A set of Fu Men mechanisms are arranged on the underface of aircraft door testpieces, and the facility of operating aircraft hatch door motion is all fixed on secondary door
In mechanism, the operating of aircraft door is driven by manipulating Fu Men mechanisms, the action of switch aircraft door is realized.
2nd, three gyroaxises are set in Fu Men mechanisms, these three gyroaxises are switched with aircraft door arm pivot post and two respectively
Door hinge rotating shaft is coaxial, and a stepper motor, the stepping controlled by computer are laid respectively at three gyroaxises of Fu Men mechanisms
Motor drives aircraft door handle and switch door hinge motion, so as to realize the switch motion of landing gate.
The technology contents and technical characterstic of the specific embodiment of the present invention are had revealed that above, it being understood, however, that in this hair
Under bright creative ideas, those skilled in the art can be to various features disclosed above and the feature not being explicitly illustrated herein
Combination make various changes and improve, but belong to protection scope of the present invention.The description of above-described embodiment be it is exemplary and
It is not restricted, protection scope of the present invention is determined by claim.
Claims (5)
1. a kind of aircraft door durability test device, aircraft door (50) includes being fixed on the aircraft cabin by arm pivot post
The handle (51) of the side of door (50), the opposite side of the aircraft door (50) is rotatably fixed to by linkage (80)
Hatch door framework (70), the linkage (80) includes being installed to the hinge rotating shaft (81) of the aircraft door (50) and is installed to
The hinge rotating shaft (82) of the hatch door framework (70), it is characterised in that
The aircraft door durability test device includes：
Load test system (10) is coordinated in microcomputer control, and it carries out whole-process control and tracking to experiment；
Stepper motor driver (20), it is received controls to coordinate the instruction of load test system (10) from the microcomputer；
Stepper motor (30), it is driven by the stepper motor driver (20), to drive the aircraft door (50) according to pre-
Fixed speed and angular movement, realize the switch motion of the aircraft door (50)；
Angular displacement sensor (40), its kinematic parameter for being used to gather the aircraft door (50) is simultaneously provided to microcomputer control
Coordinate load test system (10), the microcomputer control coordinates load test system (10) and adopts the angular displacement sensor (40)
The kinematic parameter collected controls the kinematic parameter for coordinating setting in load test system (10) to be compared with the microcomputer, with true
It is fixed whether to control the aircraft door (50) to continue to move；And
Test console, it is provided with the protection button for being used for stopping experiment.
2. aircraft door durability test device according to claim 1, it is characterised in that the aircraft door durability
Experimental rig also includes Fu Men mechanisms (60), and the Fu Men mechanisms (60) are arranged on the lower section of the aircraft door (50) to drive
The aircraft door motion.
3. aircraft door durability test device according to claim 2, it is characterised in that Fu Men mechanisms (60) bag
Include bent frame (61), the first gyroaxis (62) being arranged on the bent frame (61), the second gyroaxis (63) and the 3rd gyroaxis
(64), the stepper motor (30) include be arranged on the first gyroaxis (62) the first stepper motor (31), be arranged in second
The second stepper motor (32) on gyroaxis (63) and the 3rd stepper motor (33) being arranged on the 3rd gyroaxis (64), first
The arm pivot post of gyroaxis (62) and the aircraft door (50) is coaxially arranged, and the second gyroaxis (63) is with being installed to the aircraft
The hinge rotating shaft (81) of hatch door (50) is coaxially arranged, the 3rd gyroaxis (64) and the hinge turn for being installed to the hatch door framework (70)
Axle (82) is coaxially arranged.
4. the aircraft door durability test device according to any one of Claim 1-3, it is characterised in that described micro-
Load test system (10) is coordinated in machine control to be included control software, controls computer (11), driving stepper motor card (12) and A/D to adopt
Collect plate (13)；
The control software is used to carry out position clearing to the Fu Men mechanisms (60)；
The control computer (11) sends instruction to the driving stepper motor card (12), and the driving stepper motor card (12) will
The pulse of control parameter is sent to the stepper motor driver (20), to drive the stepper motor (30) according to control parameter
Rotation, so as to drive the aircraft door (50) to move；And
The kinematic parameter of the aircraft door (50) is supplied to A/D collection plates (13) by the angular displacement sensor (40), described
A/D collection plates (13) convert the signal into digital data transmission to the control computer (11).
5. aircraft door durability test device according to claim 1, it is characterised in that the test console is also set
Limit switches, are transfinited when aircraft door motion (50) and touch the limit switch, and the test console is automatically stopped
Experiment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710407971.1A CN107271161A (en) | 2017-06-02 | 2017-06-02 | A kind of aircraft door durability test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710407971.1A CN107271161A (en) | 2017-06-02 | 2017-06-02 | A kind of aircraft door durability test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107271161A true CN107271161A (en) | 2017-10-20 |
Family
ID=60065476
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710407971.1A Pending CN107271161A (en) | 2017-06-02 | 2017-06-02 | A kind of aircraft door durability test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107271161A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114199546A (en) * | 2021-12-13 | 2022-03-18 | 江苏恒铭达航空设备有限公司 | Durability testing device for sliding cabin door of cockpit and operation method |
| CN114235374A (en) * | 2021-12-22 | 2022-03-25 | 上海无线电设备研究所 | Durability test device and method for airplane cabin door mechanism |
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| CN105730714A (en) * | 2016-02-25 | 2016-07-06 | 陕西飞机工业（集团）有限公司 | Airplane cabin door installing and posture adjusting device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114199546A (en) * | 2021-12-13 | 2022-03-18 | 江苏恒铭达航空设备有限公司 | Durability testing device for sliding cabin door of cockpit and operation method |
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