CN110346098A - A kind of wing slow test hanging apparatus - Google Patents
A kind of wing slow test hanging apparatus Download PDFInfo
- Publication number
- CN110346098A CN110346098A CN201910602317.5A CN201910602317A CN110346098A CN 110346098 A CN110346098 A CN 110346098A CN 201910602317 A CN201910602317 A CN 201910602317A CN 110346098 A CN110346098 A CN 110346098A
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- CN
- China
- Prior art keywords
- threaded rod
- braced frame
- motor
- frame
- pedestal
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- 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.)
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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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
Abstract
The invention discloses a kind of wing slow test hanging apparatus of airplane component test related fields, including test platform Dian support platform and aircraft body, pedestal is fixedly installed in test platform upper end quadrangle, braced frame is fixedly installed in pedestal upper end, braced frame surrounding is respectively provided with fluting, lifting frame is arranged in braced frame upper end, it is connected by high-strength bolts between lifting frame at the top of braced frame, the longitudinally disposed threaded rod in braced frame inner cavity, motor is set in pedestal, weld sliding block in support platform two sides, threaded rod longitudinally runs through sliding block, and threaded rod is threadedly coupled with sliding block, fixed block is arranged in lifting frame lower end, lower end of fixing block setting lifting rope, it lifts rope lower end and suspension hook is set, the present invention is lifted by crane compared to the motor cooperation rope of transmission from upper end, the present invention program is simpler, support protection to aircraft It is more comprehensively thoughtful, the probability of cord break is reduced, whole safety is improved.
Description
Technical field
The present invention relates to airplane components to test related fields, specially a kind of wing slow test hanging apparatus.
Background technique
One of the content of aircraft wing static construction test, so as to observation and exploratory flight device structure or component in dead load
Intensity, rigidity and stress, deformation distribution situation under effect, are verifying Vehicle Structure Strength and static analysis correctness
Important means.The loading system of full size structure slow test is more complicated.Before the 1940s, when slow test, will fly
Machine, which is faced upward, to be set, and wing distributed load is simulated in bag with lead button or sand grains；It is hung on rope with iron block and simulates concentrfated load, method
It is simple and crude.Use motor machine assistor or hydraulic actuator and jack load instead later.Full size structure is quiet since the forties
Power test is all loaded by lever system, and uses coordinated multi-point loading system, guarantees that each loader can be loaded by predetermined ratio,
It can be unloaded automatically when structure is destroyed, continue to expand to avoid destruction position.70~eighties, slow test have used electronics
The automatic closed circuit Coordinated Loading System of electro-hydraulic servosystem of computer control, have a loader up to a hundred, several hundred plus
Loading point, several hundred a Measurement channels, thousands of a foil gauges, and data acquisition and processing (DAP) is carried out with electronic computer.
In the test of aircraft wing static(al), special boom hoisting is needed to lift aircraft, common boom hoisting
Rope is cooperated to be lifted by crane from upper end for heavy-duty motor, but the quality of aircraft, generally at tens tons or more, this undoubtedly increases
The hard requirement and lifting difficulty of equipment, while in experiment, need to hang weight on wing, namely increase equipment
Weight is lifted, cord break may be caused, there are some potential safety problemss.
Based on this, the present invention devises a kind of wing slow test hanging apparatus, to solve the above problems.
Summary of the invention
The purpose of the present invention is to provide a kind of wing slow test hanging apparatus, to solve to mention in above-mentioned background technique
Out the problem of.
To achieve the above object, the invention provides the following technical scheme: a kind of wing slow test hanging apparatus, including
Test platform Dian support platform and aircraft body, test platform upper end quadrangle are fixedly installed pedestal, the pedestal upper end
It is fixedly installed braced frame, the braced frame surrounding is provided with fluting, and the braced frame upper end is provided with hoisting frame
Frame is connected by high-strength bolts between the braced frame top and lifting frame, and the braced frame inner cavity is longitudinally disposed
There is threaded rod, motor is provided in the pedestal, the support platform two sides are welded with sliding block, and the sliding block extends transversely through support
The sliding slot opened up on the outside of frame, the threaded rod longitudinally runs through sliding block, and threaded rod is threadedly coupled with sliding block, the lifting frame
Lower end is provided with fixed block, and the upper end of fixing block and lifting frame inner cavity are provided with mounting plate, the fixed block welding peace
Loading board, and the mounting plate of upper end of fixing block and the mounting plate of lifting frame inner cavity pass through longitudinal grafting bolts and nuts cooperation and connect
It connects, the lower end of fixing block is provided with lifting rope, and the lifting rope lower end is provided with suspension hook.
Preferably, the test platform two sides are provided with track, the orbit connection ground and test platform upper end, and rail
Road surface is smooth.
Preferably, threaded rod upper and lower side end is provided with bearing, the threaded rod upper and lower side pass through respectively bearing with
Braced frame inner cavity top is connected with lower rotation.
Preferably, the motor power output end is fixedly connected through pedestal upper end with threaded rod bottom, and the motor is
High-power heavy industry motor, the motor running power are KW, and the preferred model JSL1115-8 of motor.
Preferably, connection ring is welded on the outside of the support platform, the connection ring and suspension hook, which cooperate, to be connected, described
Support platform upper end is provided with placing groove, and the placing groove upper end and aircraft body bottom, which cooperate, places, the placing groove
Surface uniform fold rubber layer.
Compared with prior art, the beneficial effects of the present invention are:
The present invention is being provided with two groups of heavy-duty motor driving thread spindle rotations, the cunning started by sliding block and braced frame
Slot sliding limit, realizes the lifting of support platform, is provided with before and after two groups of support platforms and is promoted to aircraft, be convenient for subsequent reality
It tests, the motor cooperation rope compared to transmission is lifted by crane from upper end, and the present invention program is simpler, protects more to the support of aircraft
Add comprehensively thoughtful, security risk is lower；
The present invention is connect by the lifting rope of disassembly installation with the connection ring on the outside of support platform after aircraft lifting,
Support platform declines a point height when driving motor inverts again, guarantees that tightening for rope of lifting is straightened, is realized using lifting rope
To the reinforcing after integral hoisting, the load of support platform is reduced, compared to traditional lifting mode, present invention reduces cord breaks
Probability, improve whole safety.
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 platform structural schematic diagram in Fig. 1 of the present invention.
In attached drawing, parts list represented by the reference numerals are as follows:
1- test platform, 101- track, 2- pedestal, 3- braced frame, 4- lifting frame, 5- high-strength bolt, 6- screw thread
Bar, 7- motor, 8- sliding block, 9- support platform, 901- connection ring, 902- placing groove, 10- fixed block, 11- mounting plate, 12- lifting
Rope, 13- suspension hook.
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. 1-3 is please referred to, the present invention provides a kind of technical solution: a kind of wing slow test hanging apparatus, including survey
Examination 1 Dian support platform 9 of platform and aircraft body, 1 upper end quadrangle of test platform are fixedly installed pedestal 2, and 2 upper end of pedestal is fixed
It is provided with braced frame 3,3 surrounding of braced frame is provided with fluting, and 3 upper end of braced frame is provided with lifting frame 4, support frame
It is connected between 3 top of frame and lifting frame 4 by high-strength bolt 5,3 inner cavity of braced frame is vertically arranged with threaded rod 6, pedestal
Motor 7 is provided in 2,9 two sides of support platform are welded with sliding block 8, and sliding block 8 extends transversely through the sliding slot opened up on the outside of braced frame 3,
Threaded rod 6 is longitudinal to run through sliding block 8, and threaded rod 6 is threadedly coupled with sliding block 8, and 4 lower end of lifting frame is provided with fixed block 10, Gu
Determine 10 upper end of block and 4 inner cavity of lifting frame is provided with mounting plate 11, fixed block 10 welds mounting plate 11, and 10 upper end of fixed block
The mounting plate 11 of 4 inner cavity of mounting plate 11 and lifting frame pass through longitudinal grafting bolts and nuts and be cooperatively connected, under fixed block 10
End is provided with lifting rope 12, and lifting 12 lower end of rope is provided with suspension hook 13.
Wherein, 1 two sides of test platform are provided with track 101, and track 101 is connected to ground and 1 upper end of test platform, and track
101 surfaces are smooth, test convenient for aircraft body is delivered to 1 upper end of test platform.6 upper and lower side end of threaded rod is provided with
Bearing, 6 upper and lower side of threaded rod pass through bearing respectively and connect with 3 inner cavity top of braced frame and lower rotation.7 power output of motor
End is fixedly connected through 2 upper end of pedestal with 6 bottom of threaded rod, and motor 7 is high-power heavy industry motor, and 7 running power of motor is
55KW, and the preferred model JSL1115-8 of motor 7.Connection ring 901, connection ring 901 and suspension hook are welded on the outside of support platform 9
13, which cooperate, connects, and 9 upper end of support platform is provided with placing groove 902,902 upper end of placing groove and aircraft body bottom phase interworking
It closes and places, 902 surface uniform fold rubber layer of placing groove can reduce the abrasion of placing groove 902 Yu aircraft contact surface.
The concrete application of the present embodiment are as follows: the present invention is moved to 1 upper end of test platform for aircraft is tested by track 101,
Two groups of heavy-duty motors 7 of starting drive two groups of threaded rods 6 to rotate in same direction simultaneously, and the sliding block 8 of 9 two sides of support platform welding is lifting
Frame 4 sliding limit under, motor 7 drive sliding block 8 with support platform 9 rise, the placing groove 902 of 9 upper end of support platform with
The docking cooperation of aircraft bottom, the rubber layer on 902 surface of placing groove can reduce the abrasion of placing groove 902 Yu aircraft contact surface, be promoted
To after certain altitude, the suspension hook 13 of lower end and the connection ring 901 in 9 outside of support platform is cooperated to connect using lifting rope 12, then
Reversion 7 supporting descending platform 9 of motor makes after lifting the holding tensional state of rope 12, closes motor and keeps whole fixed, work people
Member carries out energy test on this basis.
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 (5)
1. a kind of wing slow test hanging apparatus, including test platform (1) Dian support platform (9) and aircraft body, feature
Be: test platform (1) the upper end quadrangle is fixedly installed pedestal (2), and pedestal (2) upper end is fixedly installed support
Frame (3), braced frame (3) surrounding are provided with fluting, and braced frame (3) upper end is provided with lifting frame (4),
It is connect between lifting frame (4) by high-strength bolt (5) at the top of the braced frame (3), braced frame (3) inner cavity
It is vertically arranged with threaded rod (6), is provided with motor (7) in the pedestal (2), support platform (9) two sides are welded with sliding block
(8), the sliding block (8) extends transversely through the sliding slot opened up on the outside of braced frame (3), and the threaded rod (6) longitudinally runs through sliding block
(8), and threaded rod (6) is threadedly coupled with sliding block (8), and lifting frame (4) lower end is provided with fixed block (10), the fixation
Block (10) upper end and lifting frame (4) inner cavity are provided with mounting plate (11), and the fixed block (10) welds mounting plate (11), and
The mounting plate (11) of fixed block (10) upper end and the mounting plate (11) of lifting frame (4) inner cavity pass through longitudinal grafting bolts and nuts
It is cooperatively connected, fixed block (10) lower end is provided with lifting rope (12), and lifting rope (12) lower end is provided with suspension hook
(13)。
2. a kind of wing slow test hanging apparatus according to claim 1, it is characterised in that: the test platform
(1) two sides are provided with track (101), track (101) the connection ground and test platform (1) upper end, and track (101) surface
It is smooth.
3. a kind of wing slow test hanging apparatus according to claim 1, it is characterised in that: the threaded rod (6)
Upper and lower side end is provided with bearing, and threaded rod (6) upper and lower side passes through bearing and braced frame (3) inner cavity top and bottom respectively
Portion's rotation connection.
4. a kind of wing slow test hanging apparatus according to claim 1, it is characterised in that: the motor (7) is dynamic
Power output end is fixedly connected through pedestal (2) upper end with threaded rod (6) bottom, and the motor (7) is high-power heavy industry motor, institute
Motor (7) running power is stated as 55KW, and motor (7) preferably model JSL1115-8.
5. a kind of wing slow test hanging apparatus according to claim 1, it is characterised in that: the support platform
(9) outside is welded with connection ring (901), and the connection ring (901) and suspension hook (13) cooperate and connect, the support platform
(9) upper end is provided with placing groove (902), and placing groove (902) upper end and aircraft body bottom cooperate and place, described to put
Set slot (902) surface uniform fold rubber layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910602317.5A CN110346098A (en) | 2019-07-05 | 2019-07-05 | A kind of wing slow test hanging apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910602317.5A CN110346098A (en) | 2019-07-05 | 2019-07-05 | A kind of wing slow test hanging apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110346098A true CN110346098A (en) | 2019-10-18 |
Family
ID=68178266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910602317.5A Pending CN110346098A (en) | 2019-07-05 | 2019-07-05 | A kind of wing slow test hanging apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110346098A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111122332A (en) * | 2019-12-13 | 2020-05-08 | 上海云天联合发展有限公司 | Static test equipment |
| CN113003389A (en) * | 2021-02-20 | 2021-06-22 | 长沙航空职业技术学院 | Aircraft wing maintenance and hoist and mount auxiliary device |
| CN113340633A (en) * | 2021-05-26 | 2021-09-03 | 中国航空工业集团公司西安飞机设计研究所 | Elastic supporting device for small airplane modal test |
| CN113602525A (en) * | 2021-08-25 | 2021-11-05 | 成都飞机工业（集团）有限责任公司 | Flexible support method for catapult-assisted take-off unmanned aerial vehicle full-aircraft static test |
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| US5359542A (en) * | 1991-12-20 | 1994-10-25 | The Boeing Company | Variable parameter collision avoidance system for aircraft work platforms |
| CN102991727A (en) * | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Constraint system of airplane structure test |
| CN103487277A (en) * | 2013-10-11 | 2014-01-01 | 沈阳航空航天大学 | Multifunctional universal test bed for static test on light airplane |
| CN105444999A (en) * | 2014-08-06 | 2016-03-30 | 北京航空航天大学 | Static test loading method for long straight wings of small unmanned air vehicle |
| CN106742052A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter body slow test suspension |
| CN208119457U (en) * | 2018-04-28 | 2018-11-20 | 四川欧航科技有限责任公司 | Support frame for aircraft conversion |
| CN208471461U (en) * | 2018-07-04 | 2019-02-05 | 江苏中凯升降设备有限公司 | A kind of upright type lifting platform mechanism |
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Patent Citations (7)
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| US5359542A (en) * | 1991-12-20 | 1994-10-25 | The Boeing Company | Variable parameter collision avoidance system for aircraft work platforms |
| CN102991727A (en) * | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Constraint system of airplane structure test |
| CN103487277A (en) * | 2013-10-11 | 2014-01-01 | 沈阳航空航天大学 | Multifunctional universal test bed for static test on light airplane |
| CN105444999A (en) * | 2014-08-06 | 2016-03-30 | 北京航空航天大学 | Static test loading method for long straight wings of small unmanned air vehicle |
| CN106742052A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter body slow test suspension |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111122332A (en) * | 2019-12-13 | 2020-05-08 | 上海云天联合发展有限公司 | Static test equipment |
| CN113003389A (en) * | 2021-02-20 | 2021-06-22 | 长沙航空职业技术学院 | Aircraft wing maintenance and hoist and mount auxiliary device |
| CN113340633A (en) * | 2021-05-26 | 2021-09-03 | 中国航空工业集团公司西安飞机设计研究所 | Elastic supporting device for small airplane modal test |
| CN113340633B (en) * | 2021-05-26 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Elastic supporting device for small aircraft modal test |
| CN113602525A (en) * | 2021-08-25 | 2021-11-05 | 成都飞机工业（集团）有限责任公司 | Flexible support method for catapult-assisted take-off unmanned aerial vehicle full-aircraft static test |
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Application publication date: 20191018 |