CN105890504A - Helicopter duct deformation measuring device and method - Google Patents

Helicopter duct deformation measuring device and method Download PDF

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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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China
Prior art keywords
table bar
tail
rotor
seat
duct
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CN201610201421.XA
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Chinese (zh)
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CN105890504B (en
Inventor
于国庆
李黎明
何东旭
孔凡亮
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Harbin Aircraft Industry Group Co Ltd
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Harbin Aircraft Industry Group Co Ltd
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Priority to CN201610201421.XA priority Critical patent/CN105890504B/en
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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

A kind of helicopter duct deflection measurement apparatus and measuring method
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.
CN201610201421.XA 2016-04-01 2016-04-01 A kind of helicopter duct deflection measuring device and measuring method Active CN105890504B (en)

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

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CN105890504B CN105890504B (en) 2018-08-24

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Cited By (1)

* Cited by examiner, † Cited by third party
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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Publication number Priority date Publication date Assignee Title
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
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

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

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Cited By (2)

* Cited by examiner, † Cited by third party
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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