CN110155367A - A kind of aircraft main landing gear anti-impact force test device - Google Patents
A kind of aircraft main landing gear anti-impact force test device Download PDFInfo
- Publication number
- CN110155367A CN110155367A CN201910457712.9A CN201910457712A CN110155367A CN 110155367 A CN110155367 A CN 110155367A CN 201910457712 A CN201910457712 A CN 201910457712A CN 110155367 A CN110155367 A CN 110155367A
- Authority
- CN
- China
- Prior art keywords
- landing gear
- motor
- main landing
- support column
- impact force
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 46
- 238000005192 partition Methods 0.000 claims abstract description 12
- 230000001681 protective effect Effects 0.000 claims abstract description 12
- 238000010521 absorption reaction Methods 0.000 claims description 6
- 239000007769 metal material Substances 0.000 claims description 3
- 238000001179 sorption measurement Methods 0.000 abstract description 2
- 238000009863 impact test Methods 0.000 abstract 1
- 230000005484 gravity Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 206010057071 Rectal tenesmus Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008034 disappearance Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 230000005389 magnetism Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012372 quality testing Methods 0.000 description 1
- 208000012271 tenesmus Diseases 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a kind of aircraft main landing gear anti-impact force test devices in test flight field, including test platform and main landing gear, four groups of support columns are arranged in test platform upper end, support column longitudinally-moving grafting threaded rod, partition is arranged close to bottom in support column inner cavity, first motor is arranged in partition lower end, threaded rod is located at the portion outboard screw thread socket ring set of upper end of support column, top plate is fixedly connected between ring set, electromagnet is fixedly installed in top plate lower end, pouring weight is arranged in electromagnet lower end, the second motor is arranged in top plate upper end, motor shaft is arranged in second motor power end, motor shaft outboard end is fixedly connected with rope, link block is fixedly connected on the inside of support column, link block longitudinally opens up sliding slot, sliding plug protective door in sliding slot, the present invention is using electromagnetic adsorption weight under the height adjustment of adjustment structure, aircraft main landing gear pound to fall anti-impact Test is hit, can imitate and the quality of main landing gear before being put into use is detected.
Description
Technical field
The present invention relates to test flight field, specially a kind of aircraft main landing gear anti-impact force test device.
Background technique
Main landing gear, which is aircraft, to be parked on ground, slides, landing when, the undercarriage portion of Main Load is born in take-off and landing device
Part.In preceding two-point undercarriage, refer to mounted in the subsequent undercarriage of the center of gravity of airplane.In tail wheel type landing gear, refer to mounted in winged
Undercarriage before machine center of gravity.Refer to forward and backward undercarriage in bicycle gear.
Aircraft flight or the major support members when landing when due to main landing gear, what he needed to carry aircraft itself is
Therefore, particularly severe for the impact resistance design requirement of main landing gear to the gravity of landing Shi Geng great, each aircraft master rises
Fall frame and tested by being required to need to carry out stringent anti-impact force after the completion of production, and the design of anti-impact force test device concerning
Flight can be put into each undercarriage to use.
Therefore, market needs to design a kind of aircraft main landing gear anti-impact force test device and carries out shock resistance to main landing gear
Test, to ensure that main landing gear is up-to-standard to come into operation.
Summary of the invention
The purpose of the present invention is to provide a kind of aircraft main landing gear anti-impact force test devices, to solve above-mentioned background skill
The market proposed in art needs to design a kind of aircraft main landing gear anti-impact force test device and carries out shock resistance survey to main landing gear
Examination, with ensure main landing gear it is up-to-standard to come into operation the problem of.
To achieve the above object, the invention provides the following technical scheme: a kind of aircraft main landing gear anti-impact force test dress
It sets, including test platform and main landing gear, the main landing gear is set to test platform upper end, and the test platform front opens up
There is ramp, the test platform upper end is provided with four groups of support columns, and the support column longitudinally-moving is plugged with threaded rod, support column
Inner cavity is provided with partition close to bottom, and first motor is arranged in the partition lower end, and first motor power output end is fixedly connected
The portion outboard screw thread that threaded rod described in threaded rod is located at upper end of support column is socketed with ring set, is fixedly connected between the ring set
Top plate, the top plate lower end are fixedly installed electromagnet, and the electromagnet lower end is provided with pouring weight, and the top plate upper end is provided with
Second motor, second motor power end are provided with motor shaft, and the motor shaft outboard end is fixedly connected with rope, the support
It is fixedly connected with link block on the inside of column, the link block longitudinally offers sliding slot, and sliding plug has protective door in the sliding slot.
Preferably, the threaded rod lower end outside is provided with bearing, and threaded rod lower end is connected by bearing and partition rotation
It connects, is fixedly installed the first limited block at the top of the threaded rod.
Preferably, the pouring weight is metal material, and the pouring weight and electromagnet magnetic absorption cooperate, and the pouring weight is preferably
Cube shape structure and ball shape structure.
Preferably, second motor is double end electric machine structure, and the second motor appearance is provided with electric motor protecting frame, institute
It states electric motor protecting frame to be fixedly connected with top plate upper end, the motor shaft outer end of the second motor power output end is fixedly installed
Two limited blocks.
Preferably, protective door upper end two sides are fixedly installed engaging lug, and the engaging lug upper end is provided with link, institute
Link is stated to connect with rope.
Preferably, control panel is provided on the outside of support column described in one group, the control panel and electromagnet are electrically connected.
Compared with prior art, the beneficial effects of the present invention are:
The present invention is by the way that main landing gear to be placed on test platform, using the magnetic of control panel control electromagnet and again
Block magnetic absorption is realized by motor driven thread spindle and connection structure and is adjusted to the height of pouring weight, so that pouring weight is realized not
The different gravity generated with height tenesmus generate different impact forces to main landing gear, at the same pouring weight can be used uneven texture or
Person's pouring weight can magnetic absorption be set to the two sides of electromagnet, the anti-impact force for carrying out different directions to main landing gear is tested, and is guaranteed
It is qualified that main landing gear puts into the quality testing before actual use again；It is provided with switchable protective door in test process simultaneously, is had
Effect is isolated by the fragment generated in test process, prevents the scene of splashing from generating damage accident.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, will be described below to embodiment required
Attached drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the invention, for ability
For the those of ordinary skill of domain, without creative efforts, it can also be obtained according to these attached drawings other attached
Figure.
Fig. 1 is structure of the invention front view；
Fig. 2 is structure of the invention side view；
Fig. 3 is support column arrangement cross-sectional view in Fig. 1 of the present invention；
Fig. 4 is connecting block structure top view in Fig. 1 of the present invention；
Fig. 5 is protective door structure schematic diagram in Fig. 2 of the present invention.
In attached drawing, parts list represented by the reference numerals are as follows:
1- test platform, 2- main landing gear ontology, the ramp 3-, 4- support column, 5- threaded rod, 6- partition, 7- first motor,
The first limited block of 8-, 9- ring set, 10- top plate, 11- electromagnet, 12- pouring weight, the second motor of 13-, the second limited block of 1301-, 14-
Motor shaft, 15- rope, 16- link block, 17- sliding slot, 18- protective door, 1801- engaging lug, 1802- link, 19- control panel.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts all other
Embodiment shall fall within the protection scope of the present invention.
Fig. 1-5 is please referred to, the present invention provides a kind of technical solution: a kind of aircraft main landing gear anti-impact force test device,
Including test platform 1 and main landing gear 2, main landing gear 2 is set to 1 upper end of test platform, and 1 front of test platform offers ramp
3,1 upper end of test platform is provided with four groups of support columns 4, and 4 longitudinally-moving of support column is plugged with threaded rod 5, and 4 inner cavity of support column is close
Bottom is provided with partition 6, and first motor 7 is arranged in 6 lower end of partition, and 7 power output end of first motor is fixedly connected with threaded rod 5,
The portion outboard screw thread that threaded rod 5 is located at 4 upper end of support column is socketed with ring set 9, and top plate 10 is fixedly connected between ring set 9, top
10 lower end of plate is fixedly installed electromagnet 11, and 11 lower end of electromagnet is provided with pouring weight 12, and 10 upper end of top plate is provided with the second motor
13,13 power end of the second motor is provided with motor shaft 14, and 14 outboard end of motor shaft is fixedly connected with rope 15, consolidates on the inside of support column 4
Surely it is connected with link block 16, link block 16 is longitudinal to offer sliding slot 17, and sliding plug has protective door 18 in sliding slot 17.
Wherein, 5 lower end outside of threaded rod is provided with bearing, and 5 lower end of threaded rod is rotatablely connected by bearing and partition 6,
It drives threaded rod 5 to rotate by first motor 7, is fixedly installed the first limited block 8 at the top of threaded rod 5, prevent the rotation of ring set 9 from sliding
Fall 5 top of threaded rod.Pouring weight 12 is metal material, and pouring weight 12 and 11 magnetic absorption of electromagnet cooperate, and pouring weight 12 is preferably cube
Body contour structures and ball shape structure.Second motor 13 is double end electric machine structure, and 13 appearance of the second motor is provided with electric motor protecting frame,
Electric motor protecting frame is fixedly connected with 10 upper end of top plate, and 14 outer end of motor shaft of 13 power output end of the second motor is fixedly installed
Two limited blocks 1301.18 upper end two sides of protective door are fixedly installed engaging lug 1801, and 1801 upper end of engaging lug is provided with link
1802, link 1802 is connect with rope 15, realizes protective door 18 by rope 15 convenient for 13 drive motor shaft 14 of the second motor
Lifting opens and closes.Control panel 19 is provided on the outside of one group of support column 4, control panel 19 and electromagnet 11 are electrically connected,
The magnetic presence and disappearance of electromagnet 11 is controlled, by control panel 19 convenient for the cooperation of electromagnet 11 and weight 12.
One concrete application of the present embodiment are as follows:
Main landing gear ontology 2 is moved to 1 upper end of test platform by the ramp of 1 front setting of test platform by the present invention,
Starting the second motor 13 drives motor shaft 14 to rotate, and carries out folding and unfolding to rope 15, rope 15 connects protective door 18 and passes through two sides
The sliding slot 17 that engaging lug 1801 and link block 16 open up cooperates, and realizes 18 lifter switch of protective door to front setting, forms half
Closed test environment.According to test request, start first motor 7 and threaded rod 5 is driven to rotate, the ring set of 5 upper end of threaded rod connects
The lifting that top plate 10 realizes top plate 10 is connect, top plate 10 passes through 11 magnetic absorption pouring weight 12 of electromagnet, namely to test pouring weight 12
Height is adjusted, and when test, the energization and closing of electromagnet 11 are controlled by control panel 19, utilizes electromagnetic adsorption principle real
Existing electromagnet 11 connect with the magnetism of pouring weight 12 and disconnection, pouring weight 12 falls generate gravity after fall to main landing gear ontology 2 to it
Impact force is generated, namely completes whole test.In addition, pouring weight 12 can choose as regular pattern composite object, it also can choose and do not advise
The position of object or pouring weight 12 then can be adjusted according to testing requirement, carry out the impact force test of different aspect.
In the description of this specification, the description of reference term " one embodiment ", " example ", " specific example " etc. means
Particular features, structures, materials, or characteristics described in conjunction with this embodiment or example are contained at least one implementation of the invention
In example or example.In the present specification, schematic expression of the above terms may not refer to the same embodiment or example.
Moreover, particular features, structures, materials, or characteristics described can be in any one or more of the embodiments or examples to close
Suitable mode combines.
Present invention disclosed above preferred embodiment is only intended to help to illustrate the present invention.There is no detailed for preferred embodiment
All details are described, are not limited the invention to the specific embodiments described.Obviously, according to the content of this specification,
It can make many modifications and variations.These embodiments are chosen and specifically described to this specification, is in order to better explain the present invention
Principle and practical application, so that skilled artisan be enable to better understand and utilize the present invention.The present invention is only
It is limited by claims and its full scope and equivalent.
Claims (6)
1. a kind of aircraft main landing gear anti-impact force test device, including test platform (1) and main landing gear (2), feature exists
In: the main landing gear (2) is set to test platform (1) upper end, and test platform (1) front offers ramp (3), described
Test platform (1) upper end is provided with four groups of support columns (4), and support column (4) longitudinally-moving is plugged with threaded rod (5), support
Column (4) inner cavity is provided with partition (6) close to bottom, and first motor (7) are arranged in partition (6) lower end, and first motor (7) is dynamic
Power output end is fixedly connected threaded rod (5), and the portion outboard screw thread that the threaded rod (5) is located at support column (4) upper end is socketed with
Ring set (9) is fixedly connected with top plate (10) between the ring set (9), and top plate (10) lower end is fixedly installed electromagnet
(11), electromagnet (11) lower end is provided with pouring weight (12), and top plate (10) upper end is provided with the second motor (13), described
Second motor (13) power end is provided with motor shaft (14), and motor shaft (14) outboard end is fixedly connected rope (15), described
It is fixedly connected with link block (16) on the inside of support column (4), the link block (16) longitudinally offers sliding slot (17), the sliding slot
(17) interior sliding plug has protective door (18).
2. a kind of aircraft main landing gear anti-impact force test device according to claim 1, it is characterised in that: the screw thread
Bar (5) lower end outside is provided with bearing, and threaded rod (5) lower end is rotatablely connected by bearing and partition (6), the threaded rod
(5) top is fixedly installed the first limited block (8).
3. a kind of aircraft main landing gear anti-impact force test device according to claim 1, it is characterised in that: the pouring weight
It (12) is metal material, the pouring weight (12) and electromagnet (11) magnetic absorption cooperate, and the pouring weight (12) is preferably cube
Contour structures and ball shape structure.
4. a kind of aircraft main landing gear anti-impact force test device according to claim 1, it is characterised in that: described second
Motor (13) is double end electric machine structure, and the second motor (13) appearance is provided with electric motor protecting frame, the electric motor protecting frame with
Top plate (10) upper end is fixedly connected, and motor shaft (14) outer end of the second motor (13) power output end is fixedly installed second
Limited block (1301).
5. a kind of aircraft main landing gear anti-impact force test device according to claim 1, it is characterised in that: the protection
Door (18) upper end two sides are fixedly installed engaging lug (1801), and engaging lug (1801) upper end is provided with link (1802), institute
Link (1802) is stated to connect with rope (15).
6. a kind of aircraft main landing gear anti-impact force test device according to claim 1, it is characterised in that: described in one group
It is provided with control panel (19) on the outside of support column (4), the control panel (19) and electromagnet (11) are electrically connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910457712.9A CN110155367A (en) | 2019-05-29 | 2019-05-29 | A kind of aircraft main landing gear anti-impact force test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910457712.9A CN110155367A (en) | 2019-05-29 | 2019-05-29 | A kind of aircraft main landing gear anti-impact force test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110155367A true CN110155367A (en) | 2019-08-23 |
Family
ID=67630069
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910457712.9A Pending CN110155367A (en) | 2019-05-29 | 2019-05-29 | A kind of aircraft main landing gear anti-impact force test device |
Country Status (1)
| Country | Link |
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| CN (1) | CN110155367A (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU470725A1 (en) * | 1971-03-22 | 1975-05-15 | Предприятие П/Я В-2616 | Copier support for aircraft landing gear testing |
| KR20100084022A (en) * | 2009-01-15 | 2010-07-23 | 한국항공대학교산학협력단 | Impact and flight data analysis system for flight trainning airplane |
| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test equipment and method of air vehicle landing gear |
| CN104865040A (en) * | 2015-04-03 | 2015-08-26 | 浙江利帆家具有限公司 | Seat test machine through impact in free falling of counterweight |
| CN105136420A (en) * | 2015-09-07 | 2015-12-09 | 南京航空航天大学 | Comprehensive testing apparatus and testing method for simulating impact of arresting hook to deck and drop shock of undercarriage |
| CN105277354A (en) * | 2015-11-20 | 2016-01-27 | 高小秒 | A fixed wing aircraft landing gear testing mechanism |
| CN206177548U (en) * | 2016-10-25 | 2017-05-17 | 青岛海智检测科技有限公司 | Impact tester |
| CN206281627U (en) * | 2016-12-30 | 2017-06-27 | 宝钜(中国)儿童用品有限公司 | Children dinning chair impact test equipment |
| CN108362638A (en) * | 2017-12-06 | 2018-08-03 | 中国飞机强度研究所 | A kind of arresting system dynamic energy absorption characteristics experimental provision and experimental method |
| CN108502207A (en) * | 2018-03-19 | 2018-09-07 | 成都飞机工业（集团）有限责任公司 | Ejection impact ground validation test method |
| CN211108070U (en) * | 2019-05-29 | 2020-07-28 | 南京工业职业技术学院 | Aircraft main landing gear impact resistance testing arrangement |
-
2019
- 2019-05-29 CN CN201910457712.9A patent/CN110155367A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU470725A1 (en) * | 1971-03-22 | 1975-05-15 | Предприятие П/Я В-2616 | Copier support for aircraft landing gear testing |
| KR20100084022A (en) * | 2009-01-15 | 2010-07-23 | 한국항공대학교산학협력단 | Impact and flight data analysis system for flight trainning airplane |
| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test equipment and method of air vehicle landing gear |
| CN104865040A (en) * | 2015-04-03 | 2015-08-26 | 浙江利帆家具有限公司 | Seat test machine through impact in free falling of counterweight |
| CN105136420A (en) * | 2015-09-07 | 2015-12-09 | 南京航空航天大学 | Comprehensive testing apparatus and testing method for simulating impact of arresting hook to deck and drop shock of undercarriage |
| CN105277354A (en) * | 2015-11-20 | 2016-01-27 | 高小秒 | A fixed wing aircraft landing gear testing mechanism |
| CN206177548U (en) * | 2016-10-25 | 2017-05-17 | 青岛海智检测科技有限公司 | Impact tester |
| CN206281627U (en) * | 2016-12-30 | 2017-06-27 | 宝钜(中国)儿童用品有限公司 | Children dinning chair impact test equipment |
| CN108362638A (en) * | 2017-12-06 | 2018-08-03 | 中国飞机强度研究所 | A kind of arresting system dynamic energy absorption characteristics experimental provision and experimental method |
| CN108502207A (en) * | 2018-03-19 | 2018-09-07 | 成都飞机工业（集团）有限责任公司 | Ejection impact ground validation test method |
| CN211108070U (en) * | 2019-05-29 | 2020-07-28 | 南京工业职业技术学院 | Aircraft main landing gear impact resistance testing arrangement |
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