CN105890504A - Helicopter duct deformation measuring device and method - Google Patents
Helicopter duct deformation measuring device and method Download PDFInfo
- Publication number
- CN105890504A CN105890504A CN201610201421.XA CN201610201421A CN105890504A CN 105890504 A CN105890504 A CN 105890504A CN 201610201421 A CN201610201421 A CN 201610201421A CN 105890504 A CN105890504 A CN 105890504A
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- CN
- China
- Prior art keywords
- table bar
- tail
- rotor
- seat
- duct
- Prior art date
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/30—Measuring arrangements characterised by the use of mechanical techniques for measuring the deformation in a solid, e.g. mechanical strain gauge
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention relates to a helicopter duct deformation measuring device and method. The measuring device is simple in structure and is composed of a plurality of components. The material is aluminum, the weight is light, the operation is easy, the requirement that a force couple is applied to the center of a tail rotor is met, and the deformation measurement problem is solved. The complex work is finished by the simple method, the cost is substantially saved, and especially the problem of operation in a tiny space is solved.
Description
Technical field
The invention belongs to the test field of helicopter, particularly belong to empennage of helicopter duct deflection and measure.
Background technology
When helicopter rear carries out fatigue test, often carry out the flight load spectrum of a period of time, the nonconcentricity of duct need to be measured,
I.e. duct is relative to the deflection at tail-rotor center, and this item data is the important evidence that helicopter determines the longevity, domestic there is presently no for
The mechanism of this type of test.
The content of invention
The purpose of invention
It is an object of the invention to: a kind of helicopter duct deformation measurement measuring mechanism of design, when being exclusively used in helicopter rear fatigue test
Measure duct deflection, solve duct deflection and measure and narrow space problem.
The technology design of the present invention: designing a set of frock, tool structure is simple, it is easy to install, convenient operation, with simple side
Method completes the work of complexity.
Technical scheme
A kind of helicopter duct deflection measurement apparatus is provided, this device include tail-rotor bogusware connect end (1), measure adjust district (2),
Tail-rotor center torque axle (3), table bar fix seat (4), ring for fixing (5), table bar connection seat (6), table bar rotating shaft (7), table
Bar alignment pin (8), table bar (9), dial gauge (10), dial gauge fixed frame (11) and couple loading end (12);
Described tail-rotor bogusware connects end (1) and is used for being connected with tail-rotor bogusware, and tail-rotor center torque axle (3) is Step Shaft, carefully
Axle head is connected the fixing connection of end (1) with tail-rotor bogusware, and thick axle head is as couple loading end (12);
The table bar described in thin axle sleeve dress of tail-rotor center torque axle (3) fixes seat (4) and two ring for fixings (5), wherein said
Table bar fix seat (4) and be positioned between two ring for fixings (5),
Ring for fixing (5) is used for adjusting table bar and fixes the seat (4) axial location on thin axle,
Seat (4) fixed by table bar is upper and lower two bearing shells composition, and the upper surface of top bearing shell is a plane, and this plane is fixing connects institute
The table bar stated connects seat (6),
Table bar (9) lower end is connected seat (6) by table bar rotating shaft (7) and is rotationally connected with table bar, and table bar (9) is with table bar even
Positioned by table bar alignment pin (8) between joint chair (6),
Table bar (9) upper end is fixed with dial gauge fixed frame (11), and dial gauge (10) is arranged in dial gauge fixed frame (11).
Ring for fixing (5) is that jackscrew is fixed or flexible fastening.
Provide the measuring method of a kind of helicopter duct deflection measurement apparatus, use above-mentioned helicopter duct deflection to measure
Device,
After described tail-rotor bogusware is installed on tail-rotor duct, then tail-rotor bogusware connection end (1) is connected with tail-rotor bogusware,
Make dial gauge (10) the indicator top of described helicopter duct deflection measurement apparatus to tail-rotor duct inwall;
Carry out helicopter rear fatigue test, repetitive measurement duct deflection in the middle of fatigue test.
Particularly, measurement point distribution was at one week of duct.
The effect of invention
The effect of the present invention: on the basis of applying tail-rotor couple frock, it is achieved the measurement of duct deflection, mechanism uses aluminum
Material, is made up of multiple unit constructions, lightweight, and in solving small space, frock is installed and a difficult problem for operation.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention;
Fig. 2 is the side view of the present invention;
Wherein: 1-tail-rotor bogusware connects end, 2-measure adjust district, seat fixed by 3-tail-rotor center torque axle, 4-table bar, 5-ring for fixing,
6-table bar connects seat, 7-table bar rotating shaft, 8-table bar alignment pin, 9-table bar, 10-dial gauge, 11-dial gauge fixed frame, 12 couples
Loading end.
Detailed description of the invention
A kind of helicopter duct deflection measurement apparatus is provided, this device include tail-rotor bogusware connect end (1), measure adjust district (2),
Tail-rotor center torque axle (3), table bar fix seat (4), ring for fixing (5), table bar connection seat (6), table bar rotating shaft (7), table
Bar alignment pin (8), table bar (9), dial gauge (10), dial gauge fixed frame (11) and couple loading end (12);
Described tail-rotor bogusware connects end (1) and is used for being connected with tail-rotor bogusware, and tail-rotor center torque axle (3) is Step Shaft, carefully
Axle head is connected the fixing connection of end (1) with tail-rotor bogusware, and thick axle head is as couple loading end (12);
The table bar described in thin axle sleeve dress of tail-rotor center torque axle (3) fixes seat (4) and two ring for fixings (5), wherein said
Table bar fix seat (4) and be positioned between two ring for fixings (5),
Ring for fixing (5) is used for adjusting table bar and fixes the seat (4) axial location on thin axle,
Seat (4) fixed by table bar is upper and lower two bearing shells composition, and the upper surface of top bearing shell is a plane, and this plane is fixing connects institute
The table bar stated connects seat (6),
Table bar (9) lower end is connected seat (6) by table bar rotating shaft (7) and is rotationally connected with table bar, and table bar (9) is with table bar even
Positioned by table bar alignment pin (8) between joint chair (6),
Table bar (9) upper end is fixed with dial gauge fixed frame (11), and dial gauge (10) is arranged in dial gauge fixed frame (11).
Ring for fixing (5) is that jackscrew is fixed or flexible fastening.
The measuring method of above-mentioned a kind of helicopter duct deflection measurement apparatus, uses above-mentioned helicopter duct deflection to measure
Device,
After described tail-rotor bogusware is installed on tail-rotor duct, then tail-rotor bogusware connection end (1) is connected with tail-rotor bogusware,
Make dial gauge (10) the indicator top of described helicopter duct deflection measurement apparatus to tail-rotor duct inwall;
Carry out helicopter rear fatigue test, repetitive measurement duct deflection in the middle of fatigue test.
Particularly, measurement point distribution was at one week of duct.
Claims (3)
1. a helicopter duct deflection measurement apparatus, this device include tail-rotor bogusware connect end (1), measure adjust district (2),
Tail-rotor center torque axle (3), table bar fix seat (4), ring for fixing (5), table bar connection seat (6), table bar rotating shaft (7), table
Bar alignment pin (8), table bar (9), dial gauge (10), dial gauge fixed frame (11) and couple loading end (12);
Described tail-rotor bogusware connects end (1) and is used for being connected with tail-rotor bogusware, and tail-rotor center torque axle (3) is Step Shaft, carefully
Axle head is connected the fixing connection of end (1) with tail-rotor bogusware, and thick axle head is as couple loading end (12);
The table bar described in thin axle sleeve dress of tail-rotor center torque axle (3) fixes seat (4) and two ring for fixings (5), wherein said
Table bar fix seat (4) and be positioned between two ring for fixings (5),
Ring for fixing (5) is used for adjusting table bar and fixes the seat (4) axial location on thin axle,
Seat (4) fixed by table bar is upper and lower two bearing shells composition, and the upper surface of top bearing shell is a plane, and this plane is fixing connects institute
The table bar stated connects seat (6),
Table bar (9) lower end is connected seat (6) by table bar rotating shaft (7) and is rotationally connected with table bar, and table bar (9) is with table bar even
Positioned by table bar alignment pin (8) between joint chair (6),
Table bar (9) upper end is fixed with dial gauge fixed frame (11), and dial gauge (10) is arranged in dial gauge fixed frame (11).
Ring for fixing (5) is that jackscrew is fixed or flexible fastening.
2. a measuring method for helicopter duct deflection measurement apparatus, uses the helicopter duct deformation described in claim
Measuring device,
After described tail-rotor bogusware is installed on tail-rotor duct, then tail-rotor bogusware connection end (1) is connected with tail-rotor bogusware,
Make dial gauge (10) the indicator top of described helicopter duct deflection measurement apparatus to tail-rotor duct inwall;
Carry out helicopter rear fatigue test, repetitive measurement duct deflection in the middle of fatigue test.
The measuring method of a kind of helicopter duct deflection measurement apparatus the most according to claim 1, it is characterised in that:
Measurement point distribution was at one week of duct.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201610201421.XA CN105890504B (en) | 2016-04-01 | 2016-04-01 | A kind of helicopter duct deflection measuring device and measuring method |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201610201421.XA CN105890504B (en) | 2016-04-01 | 2016-04-01 | A kind of helicopter duct deflection measuring device and measuring method |
Publications (2)
Publication Number | Publication Date |
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CN105890504A true CN105890504A (en) | 2016-08-24 |
CN105890504B CN105890504B (en) | 2018-08-24 |
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CN201610201421.XA Active CN105890504B (en) | 2016-04-01 | 2016-04-01 | A kind of helicopter duct deflection measuring device and measuring method |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109720566A (en) * | 2017-10-31 | 2019-05-07 | 一飞智控(天津)科技有限公司 | The main rotor control system of the unmanned device of manned helicopter |
Citations (8)
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CN102589399A (en) * | 2011-12-31 | 2012-07-18 | 太原重工股份有限公司 | Measuring device for sealing surface of flange |
CN202452945U (en) * | 2011-12-30 | 2012-09-26 | 成都环球特种玻璃制造有限公司 | Novel measuring device for deformation of toughened glass insulator |
CN104019970A (en) * | 2014-05-20 | 2014-09-03 | 北京航空航天大学 | Testing system for testing fatigue performance of helicopter tail rotor |
CN104374570A (en) * | 2014-11-24 | 2015-02-25 | 中国航空动力机械研究所 | Method for gaining service life of helicopter drive system component |
CN105241631A (en) * | 2015-11-04 | 2016-01-13 | 中航维拓(北京)科技有限责任公司 | Helicopter tail rotor vortex ring state testing system |
CN204988096U (en) * | 2015-09-11 | 2016-01-20 | 中国第一汽车股份有限公司 | Mould slip rotation measurement device |
CN105319039A (en) * | 2014-07-02 | 2016-02-10 | 西安航空动力股份有限公司 | Vibration fatigue testing method for large-bypass-ratio engine fan blade with shoulder |
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2016
- 2016-04-01 CN CN201610201421.XA patent/CN105890504B/en active Active
Patent Citations (8)
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DE202005001116U1 (en) * | 2005-01-12 | 2005-09-15 | Glas Heinz Gmbh | Measuring device for measuring ductility in inserted carrying compartments made from injection-molded plastic has a displacement transducer and a load-impinged movable deformation strut |
CN202452945U (en) * | 2011-12-30 | 2012-09-26 | 成都环球特种玻璃制造有限公司 | Novel measuring device for deformation of toughened glass insulator |
CN102589399A (en) * | 2011-12-31 | 2012-07-18 | 太原重工股份有限公司 | Measuring device for sealing surface of flange |
CN104019970A (en) * | 2014-05-20 | 2014-09-03 | 北京航空航天大学 | Testing system for testing fatigue performance of helicopter tail rotor |
CN105319039A (en) * | 2014-07-02 | 2016-02-10 | 西安航空动力股份有限公司 | Vibration fatigue testing method for large-bypass-ratio engine fan blade with shoulder |
CN104374570A (en) * | 2014-11-24 | 2015-02-25 | 中国航空动力机械研究所 | Method for gaining service life of helicopter drive system component |
CN204988096U (en) * | 2015-09-11 | 2016-01-20 | 中国第一汽车股份有限公司 | Mould slip rotation measurement device |
CN105241631A (en) * | 2015-11-04 | 2016-01-13 | 中航维拓(北京)科技有限责任公司 | Helicopter tail rotor vortex ring state testing system |
Non-Patent Citations (1)
Title |
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余忠烜等: "直11型直升机旋翼***动部件飞行载荷测试技术", 《直升机技术》 * |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109720566A (en) * | 2017-10-31 | 2019-05-07 | 一飞智控(天津)科技有限公司 | The main rotor control system of the unmanned device of manned helicopter |
CN109720566B (en) * | 2017-10-31 | 2024-03-01 | 一飞智控(天津)科技有限公司 | Main rotor control system of unmanned device of manned helicopter |
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CN105890504B (en) | 2018-08-24 |
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