CN109969428A - A kind of aircraft nose landing gear uplock reliability and static strength/rigidity integrated experiment device and method - Google Patents
A kind of aircraft nose landing gear uplock reliability and static strength/rigidity integrated experiment device and method Download PDFInfo
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- CN109969428A CN109969428A CN201910380974.XA CN201910380974A CN109969428A CN 109969428 A CN109969428 A CN 109969428A CN 201910380974 A CN201910380974 A CN 201910380974A CN 109969428 A CN109969428 A CN 109969428A
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- stand
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- 238000002474 experimental method Methods 0.000 title claims abstract description 44
- 230000003068 static effect Effects 0.000 title claims abstract description 22
- 238000000034 method Methods 0.000 title abstract description 5
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 20
- 238000012360 testing method Methods 0.000 claims description 40
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 230000001960 triggered effect Effects 0.000 claims description 3
- 238000010998 test method Methods 0.000 claims 1
- 230000006870 function Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000004088 simulation Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000007659 motor function Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Classifications
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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
Abstract
The present invention proposes a kind of aircraft nose landing gear uplock reliability and static strength/rigidity integrated experiment device and method, and corresponding load can be loaded according to actual condition, and the experimental data of reliability also be more nearly objective requirement.The integrated experiment device, including stand for experiment, uplock, load driver module and lock ring module；Uplock is fixedly installed on the crossbeam of stand for experiment；In lock ring module, lock ring pedestal has bottom surface and two sides auricle, and lock ring both ends pass through lock ring base body and are fixedly connected respectively with the two sides auricle of lock ring pedestal；Pillar one end is fixedly connected with lock ring base body far from one end of lock ring, and the side of the other end and stand for experiment pivotally connects；Load driver module includes pressurized strut and pressure sensor, and the fixing end of pressurized strut and the bottom of stand for experiment pivotally connect, and the working end of pressurized strut is fixedly connected through pressure sensor with the bottom surface of lock ring pedestal.
Description
Technical field
The present invention relates to air equipment uplock reliability test technical fields, and in particular to one kind before aircraft for rising and falling
Frame uplock accurately loads the experimental rig and method of load.
Background technique
Landing gear uplock for airplanes is used to lock or unlock all kinds of movement mechanisms on aircraft, is Aircraft landing gear system
Important spare part is the critical product that can relationship undercarriage work normally.Its with weight, small in size, static strength require it is high,
The features such as precise structure degree is big.In normal flight, uplock should be able to normal switching-off, and be maintained at normal locking state or normal
It opens, otherwise can cause aircraft mission failure, and influence Flight Safety.Especially in the aircraft landing stage, if uplock
It cannot normally open, will lead to undercarriage cannot normally put down, it is most likely that cause the major accidents such as air crash.Therefore, it is
The reliability index of assessment landing gear uplock, improves reliability level, carries out in laboratory environments to uplock reliable
Property test be very necessary.
Since uplock reliability test needs to consider the composite factors such as vibration, height epidemic disaster, hydraulic, do not require nothing more than
Experimental rig has lesser volume, weight and biggish rigidity, can be carried out the simulation of uplock motor function, is guarantee test
The reliability of device itself, the structure and function principle of experimental rig also should be simple as far as possible.In addition, during locking, unlocking
Load of the lock ring load on latch hook is to influence uplock to open/one of locking function and the key factor of reliability, it is necessary to
The adjustment of latch hook load is realized during the test.
It is reliable that Chinese patent literature CN107084834A discloses a kind of uplock for being able to achieve the adjustment of lock ring lateral position
Property experimental rig, Chinese patent literature CN103983443A is disclosed a kind of to be tried for undercarriage hatch door uplock reliability
The horizontal test device tested ".Above-mentioned two scenario-frame is complex, and all can be only done the reliability of locking and unlocking function
Test, and cannot achieve the accurate load of load, to be difficult to reflect the reliability of uplock under the conditions of live flying.
Conventional static strength/stiffness test is to be fixed on uplock on universal testing machine in fact by a set of dedicated fixture
It applies, but the power thrusts of universal testing machine are relatively-stationary, therefore also cannot achieve the accurate simulation of static strength/rigidity.
Summary of the invention
In order to enable uplock reliability test more comprehensively, be truly reflected practical application scene, rather than just
Only complete the reliability test of unlocking, locking function, the present invention proposes a kind of aircraft nose landing gear uplock reliability and quiet strong
Degree/rigidity integrated experiment device can load corresponding load, the also more adjunction of the experimental data of reliability according to actual condition
Nearly objective requirement.
Technical scheme is as follows:
A kind of aircraft nose landing gear uplock reliability and static strength/rigidity integrated experiment device, including stand for experiment,
Uplock, load driver module and lock ring module；
The uplock is fixedly installed on the crossbeam of stand for experiment；
The lock ring module includes lock ring, lock ring base body, lock ring pedestal and pillar；Wherein, lock ring pedestal have bottom surface and
Two sides auricle, lock ring both ends pass through lock ring base body and are fixedly connected respectively with the two sides auricle of lock ring pedestal；Pillar one end and lock ring
Base body is fixedly connected far from one end of lock ring, and the side of the other end and stand for experiment pivotally connects；
The load driver module includes pressurized strut and pressure sensor, the fixing end of pressurized strut and the bottom of stand for experiment
Pivotally connect, the working end of pressurized strut is fixedly connected through pressure sensor with the bottom surface of lock ring pedestal, lock ring with
Uplock latch hook meets locking and positional relationship required by unlocking function.
Based on above scheme, the present invention has also further made following optimization:
Uplock can be specifically fixedly connected by uplock mounting rack with the crossbeam of stand for experiment.
Pillar one end can be specifically fixedly connected with lock ring base body far from one end of lock ring by coaxial connecting rod.
Lock ring base body have two sides auricle, lock ring both ends pass through lock ring base body two sides auricle respectively with lock ring pedestal two
Piece of picking up the ears is fixedly connected.Certainly, lock ring base body can also be using other possible more complicated shape and structures, as long as not influencing to lock
Clasp joint touches lock ring.
Installation for load driver module, can specifically increase a pressurized strut mounting base, and pressurized strut mounting base is fixed
It is installed on the bottom of stand for experiment, the fixing end and pressurized strut mounting base of pressurized strut are hinged.It is of course also possible in stand for experiment
Bottom straight forming a pair of auricle, for installing pressurized strut.
Installation for pillar specifically can be arranged a pair of of auricle in the side of stand for experiment, be provided with pin hole on auricle,
Pillar is mounted between a pair of of auricle by pin.This pair of of auricle, which can be, to be directly molded in stand for experiment, is also possible to
In addition adding and be fixedly installed in stand for experiment, it is equivalent to pillar mounting base.
Based on apparatus above structure, stand for experiment can be reinforced, using the pressure sensor of enough precisions, thus not
It is only applicable to reliability test, is also applied for static strength/stiffness test.
Reliability test the following steps are included:
A1) original state: latch hook is located at opening state, and lock ring is located at predetermined position；
A2) oil pressure compression system pressure supply, the piston rod of pressurized strut, which stretches out, drives lock ring to move upwards, and latch hook is main after being triggered
It is dynamic to close, when the pressure of pressure sensor reaches the load value of setting, setting duration is kept in this state；
A3 the piston rod of) oil pressure compression system pressure supply, pressurized strut generates downward pulling force to lock ring, when pulling force reaches setting
When load value, setting duration is kept in this state；
A4) control uplock is unlocked, and the piston rod of pressurized strut, which is shunk, drives lock ring to move back into predetermined position；
Repeat above step a2)-step a4) reach the number of setting, complete reliability test；
Static strength/stiffness test the following steps are included:
B) load test that gear up uplock is born
B1 uplock adjustment) is in locked state；
B2 it) gradually upwards pressure to the application of uplock latch hook, when reaching setting pressure, keeps setting in this case
Duration；
B3 experimental conditions) are recorded, by the discharge degree of uplock；
C) load test that gear down uplock is born
C1 uplock adjustment) is in locked state；
C2) gradually apply downward pulling force to uplock latch hook, when reaching setting pulling force, keep setting in this case
Duration；
C3 experimental conditions) are recorded, the pulling force of uplock is unloaded；
So far, static strength/stiffness test is completed.
The invention has the following advantages:
1, static strength/stiffness test and reliability test are incorporated into a test-bed, be sufficiently contemplated dynamics and
Two, direction factor, can apply load according to actual condition, and experimental data has more referential.
2, by setting pressure sensor, and pressure sensor is connect with lock ring structure, so that latch hook load feedback arrives
Control system, to more accurately complete the reliability test of landing gear uplock according to actual design index.
3, overall structure is concise, it is easy to realize, cost is relatively low for compbined test.
Detailed description of the invention
Fig. 1 is floor map of the experimental rig in locked state.
Fig. 2 is the thin portion schematic diagram of lock ring dependency structure.
Fig. 3, Fig. 4 are the stereoscopic schematic diagram of the experimental rig two different perspectivess in locked state.
Fig. 5 is floor map of the experimental rig in unlocking condition.
Fig. 6, Fig. 7 are the stereoscopic schematic diagram of the experimental rig two different perspectivess in unlocking condition.
Fig. 8 is the overall system architecture schematic diagram of uplock reliability test.
Drawing reference numeral explanation:
1- stand for experiment, 2- uplock mounting rack, 3- uplock, 4- pillar, 5- pressure sensor, 6- lock ring, 7- are (upper
Lock) latch hook, 8- pressurized strut, 9- lock ring pedestal, 10- pressurized strut mounting base, 11- stand for experiment auricle (pillar mounting base), 12-
Lock ring base body, 13- connecting rod.
Specific embodiment
It elaborates with reference to the accompanying drawing to the present invention.
As shown in Fig. 1-Fig. 7, which can be mainly divided into experimental stand, lock ring module and load driver module three
Part.Uplock is mounted on experimental stand, and lock ring module and load driver module are set to the interior zone of experimental stand.Tool
For body:
Experimental stand includes stand for experiment 1 and uplock mounting rack 2, and uplock mounting rack is mounted on experiment branch by screw
On the crossbeam of frame, uplock is mounted on uplock mounting rack.
Lock ring module includes lock ring 6, lock ring base body 12, connecting rod 13, lock ring pedestal 9 and pillar 4.Lock ring pedestal has bottom
Face and two sides auricle, lock ring base body also have a two sides auricle, 6 both ends of lock ring pass through the two sides auricle of lock ring base body 12 respectively with lock
The two sides auricle of ring pedestal 9 is fixedly connected.It is also provided with a pair of of auricle on the right side of stand for experiment, pin is respectively set on a pair of of auricle
The right end in hole, pillar 4 is mounted between a pair of of auricle by pin, and lock ring base body 12 passes through the left end of connecting rod 13 and pillar 4
Connection.There is screw thread at the both ends of connecting rod 13, and one end is mounted in the threaded hole of pillar 4, by the connection for configuring different length
Bar, the distance of adjustable lock ring to stand for experiment auricle, to adjust the actuation direction (angle) of load driver module.
Load driver module includes pressurized strut 8, pressurized strut mounting base 10 and pressure sensor 5, and pressurized strut mounting base 10 is welded
It connects in stand for experiment, 8 one end of pressurized strut is connected in pressurized strut mounting base 10 by pin, and the other end passes through screw and pressure
Sensor 5 connects, and pressure sensor 5 and the underrun screw of lock ring pedestal 9 are fixed.
The hinge joint self-assembling formation stable triangular structure of lock ring 6, the hinge joint of pressurized strut fixing end and pillar right end, lock
Angle where ring is usually obtuse angle.The pull rod of pressurized strut 8 is flexible to drive lock ring pedestal 9 to move, and lock ring pedestal 9 drives lock ring base body
12 move in a circle around stand for experiment auricle 11, at the same lock ring pump can touch latch hook 7 complete unlock, locking function
Energy.
Failtests:
Step 1: before locking, latch hook 7 is located at opening state, and lock ring 6 is located at predetermined position.
Step 2: when locking, 8 pressure supply chamber pressure supply of pressurized strut, the piston rod of pressurized strut 8, which stretches out, drives lock ring 6 to move upwards,
After uplock is triggered, latch hook 7 is actively closed, when the pressure of pressure sensor reaches true flight load value, in this shape
State is kept for 3 seconds.
Step 3: after uplock is closed, giving 8 oil back chamber pressure supply of pressurized strut, the piston rod of pressurized strut 8 generates downwards lock ring 6
Pulling force is kept for 3 seconds when pulling force reaches the true flight load value of uplock in this state.
Step 4: control uplock is unlocked, and the piston rod of pressurized strut 8, which is shunk, drives lock ring 6 to move to predetermined position.
The number that step 2- step 4 reaches setting is repeated, uplock reliability test is completed.The structure of the experimental rig is set
The positional relationship of the meter sufficiently practical nose-gear uplock of simulation, uplock locking and the direction and true working condition unlocked
It is consistent.
The working principle of total system controls signal as shown in figure 8, console is issued to oil pressure loading system, controls respectively
Pressurized strut and uplock movement.Pressure sensor is used to measure the load load of uplock.The pressure sensor on pressurized strut head
Force signal and other detection signals are fed back to console.Nose-gear uplock body portion is mounted on bed stand
On crossbeam.The piston rod head of pressurized strut is equipped with high-precision pressure sensor, and the lock ring positioned at post tips passes through lock ring bottom
Seat is connect with pressure sensor.Stretched by the piston rod of pressurized strut drive pillar rotation and pack up simulating nose-gear realization,
Put down movement.
The present apparatus can also carry out static strength/Rigidity Experiment, and the test content of experiment includes:
1) nose-gear packs up the load test of uplock receiving
1.1) uplock adjustment is in locked state.
1.2) by the way that gradually the application of landing gear uplock latch hook upwards pressure forward, when pressure reaches setting value,
This pressure state keeps setting time, and upper lock construction should not destroy during this period of time.
1.3) after the completion of uplock strain-gauge test data record, the discharge degree of uplock is fallen.
2) nose-gear puts down the load test of uplock receiving
2.1) uplock adjustment is in locked state.
2.2) by the way that gradually landing gear uplock latch hook applies downward pulling force forward, when pulling force reaches setting value,
This state of tension keeps setting time, and upper lock construction should not destroy during this period of time.
2.3) after the completion of uplock strain-gauge test data record, the pulling force of uplock is uninstalled.
Claims (7)
1. a kind of aircraft nose landing gear uplock reliability and static strength/rigidity integrated experiment device, it is characterised in that: including
Stand for experiment, uplock, load driver module and lock ring module；
The uplock is fixedly installed on the crossbeam of stand for experiment；
The lock ring module includes lock ring, lock ring base body, lock ring pedestal and pillar；Wherein, lock ring pedestal has bottom surface and two sides
Auricle, lock ring both ends pass through lock ring base body and are fixedly connected respectively with the two sides auricle of lock ring pedestal；Pillar one end and lock ring base body
One end far from lock ring is fixedly connected, and the side of the other end and stand for experiment pivotally connects；
The load driver module includes pressurized strut and pressure sensor, and the bottom of the fixing end of pressurized strut and stand for experiment is with can
The mode of rotation connects, and the working end of pressurized strut is fixedly connected through pressure sensor with the bottom surface of lock ring pedestal, lock ring with it is upper
It locks latch hook and meets locking and positional relationship required by unlocking function.
2. aircraft nose landing gear uplock reliability according to claim 1 and static strength/rigidity integrated experiment device,
It is characterized by: the uplock is fixedly connected by uplock mounting rack with the crossbeam of stand for experiment.
3. aircraft nose landing gear uplock reliability according to claim 1 and static strength/rigidity integrated experiment device,
It is characterized by: described pillar one end is fixedly connected with lock ring base body far from one end of lock ring by coaxial connecting rod.
4. aircraft nose landing gear uplock reliability according to claim 1 and static strength/rigidity integrated experiment device,
It is characterized by: the lock ring base body also has a two sides auricle, lock ring both ends pass through the two sides auricle of lock ring base body respectively with lock
The two sides auricle of ring pedestal is fixedly connected.
5. aircraft nose landing gear uplock reliability according to claim 1 and static strength/rigidity integrated experiment device,
It is characterized by: the load driver module further includes pressurized strut mounting base, pressurized strut mounting base is fixedly installed in stand for experiment
Bottom, the fixing end and pressurized strut mounting base of pressurized strut be hinged.
6. aircraft nose landing gear uplock reliability according to claim 1 and static strength/rigidity integrated experiment device,
It is characterized by: the side of the stand for experiment is provided with a pair of of auricle, pin hole is provided on auricle, pillar is installed by pin
Between a pair of of auricle.
7. based on aircraft nose landing gear uplock reliability described in claim 1 and static strength/rigidity integrated experiment device
Test method, which is characterized in that including reliability test and static strength/stiffness test；
The reliability test the following steps are included:
A1) original state: latch hook is located at opening state, and lock ring is located at predetermined position；
A2) oil pressure compression system pressure supply, the piston rod of pressurized strut, which stretches out, drives lock ring to move upwards, and latch hook actively closes after being triggered
It closes, when the pressure of pressure sensor reaches the load value of setting, keeps setting duration in this state；
A3 the piston rod retraction of) oil pressure compression system pressure supply, pressurized strut generates downward pulling force to lock ring, when pulling force reaches setting
When load value, setting duration is kept in this state；
A4) control uplock is unlocked, and the piston rod of pressurized strut, which is shunk, drives lock ring to move back into predetermined position；
Repeat above step a2)-step a4) reach the number of setting, complete reliability test；
Static strength/the stiffness test the following steps are included:
B) nose-gear packs up the load test of uplock receiving
B1 uplock adjustment) is in locked state；
B2 it) gradually upwards pressure to the application of uplock latch hook, when reaching setting pressure, when keeping setting in this case
It is long；
B3 experimental conditions) are recorded, by the discharge degree of uplock；
C) nose-gear puts down the load test of uplock receiving
C1 uplock adjustment) is in locked state；
C2) gradually apply downward pulling force to uplock latch hook, when reaching setting pulling force, when keeping setting in this case
It is long；
C3 experimental conditions) are recorded, the pulling force of uplock is unloaded；
So far, static strength/stiffness test is completed.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910150451 | 2019-02-28 | ||
| CN2019101504516 | 2019-02-28 |
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| Publication Number | Publication Date |
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| CN109969428A true CN109969428A (en) | 2019-07-05 |
| CN109969428B CN109969428B (en) | 2024-03-29 |
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|---|---|---|---|
| CN201910380974.XA Active CN109969428B (en) | 2019-02-28 | 2019-05-08 | Test method of comprehensive test device for reliability and static strength/rigidity of upper lock of nose landing gear of airplane |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110815078A (en) * | 2019-11-14 | 2020-02-21 | 昌河飞机工业（集团）有限责任公司 | Undercarriage strut test clamping device and method |
| CN113639909A (en) * | 2021-07-01 | 2021-11-12 | 东风柳州汽车有限公司 | Engine cover pulling-out force testing device |
| CN114261533A (en) * | 2021-12-31 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear pneumatic load simulation device |
| CN114383934A (en) * | 2022-01-10 | 2022-04-22 | 中航飞机起落架有限责任公司 | Loading device and method for hook-and-loop lock ring test of landing gear |
| CN114813000A (en) * | 2022-06-23 | 2022-07-29 | 中国飞机强度研究所 | Load monitoring device and method for buffeting test of aircraft key structure |
| CN115195998A (en) * | 2022-09-16 | 2022-10-18 | 成都纵横大鹏无人机科技有限公司 | Undercarriage winding and unwinding devices and aircraft |
| CN115979697A (en) * | 2023-03-17 | 2023-04-18 | 西安航天动力研究所 | Frame multiplex condition test device |
| CN114261533B (en) * | 2021-12-31 | 2024-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic load simulator of aircraft landing gear |
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| CN209905103U (en) * | 2019-02-28 | 2020-01-07 | 西安生淼机电科技有限责任公司 | Comprehensive test device for reliability and static strength/rigidity of aircraft nose landing gear uplock |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110815078A (en) * | 2019-11-14 | 2020-02-21 | 昌河飞机工业（集团）有限责任公司 | Undercarriage strut test clamping device and method |
| CN113639909A (en) * | 2021-07-01 | 2021-11-12 | 东风柳州汽车有限公司 | Engine cover pulling-out force testing device |
| CN114261533A (en) * | 2021-12-31 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear pneumatic load simulation device |
| CN114261533B (en) * | 2021-12-31 | 2024-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic load simulator of aircraft landing gear |
| CN114383934A (en) * | 2022-01-10 | 2022-04-22 | 中航飞机起落架有限责任公司 | Loading device and method for hook-and-loop lock ring test of landing gear |
| CN114383934B (en) * | 2022-01-10 | 2023-11-21 | 中航飞机起落架有限责任公司 | Landing gear hook ring lock ring test loading device and method |
| CN114813000A (en) * | 2022-06-23 | 2022-07-29 | 中国飞机强度研究所 | Load monitoring device and method for buffeting test of aircraft key structure |
| CN115195998A (en) * | 2022-09-16 | 2022-10-18 | 成都纵横大鹏无人机科技有限公司 | Undercarriage winding and unwinding devices and aircraft |
| CN115195998B (en) * | 2022-09-16 | 2022-12-23 | 成都纵横大鹏无人机科技有限公司 | Undercarriage winding and unwinding devices and aircraft |
| CN115979697A (en) * | 2023-03-17 | 2023-04-18 | 西安航天动力研究所 | Frame multiplex condition test device |
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