CN106767651B - A kind of measurement method of helicopter blade established angle - Google Patents
A kind of measurement method of helicopter blade established angle Download PDFInfo
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- CN106767651B CN106767651B CN201611075469.7A CN201611075469A CN106767651B CN 106767651 B CN106767651 B CN 106767651B CN 201611075469 A CN201611075469 A CN 201611075469A CN 106767651 B CN106767651 B CN 106767651B
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- established angle
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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
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes
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Abstract
The invention discloses a kind of measurement methods of helicopter blade established angle, belong to helicopter the field of test technology.The following steps are included: Step 1: the ground based terminal of sensor and sensor is connected；Step 2: first sensor is fixed in the first mounting bracket, the first mounting bracket is installed by blade clamping plate；Second sensor is fixed in the second mounting bracket, keeps consistent with first sensor measurement axis direction, by installing the second mounting bracket in center piece；Step 3: collective-pitch lever, control stick, pedal are placed in base position, propeller hub support arm is placed in four different orientations respectively, records the wing setting angle of measurement respectively by ground based terminal, checks whether main blade taper meets the requirements；Step 4: carrying out main pitch established angle variation inspection respectively after main blade taper is met the requirements, the period established angle variation of main paddle longitudinal direction checks, the lateral period established angle of main paddle changes inspection.The present invention can be realized once mounting, repeatedly measurement, improve guarantee efficiency.
Description
Technical field
The invention belongs to helicopter the field of test technology, and in particular to a kind of measurement method of helicopter blade established angle.
Background technique
After component (such as booster, steering engine) is installed on machine or replaced to helicopter flight steerable system, need to system
Work is adjusted and checks, to confirm whether the specific manipulation device of helicopter (control stick, collective-pitch lever, pedal) position corresponds to
In specific wing setting angle.The especially measurement of wing setting angle, accuracy are directly related to the flying quality of helicopter
And flight quality.
Traditional wing setting angle measurement, which generallys use, carves the measurement of position instrument, and the wing setting angle of propeller shank is measured by it
For angle with horizontal plane to determine whether meeting flight control system design requirement, principle is that position instrument mounting surface and water are carved in measurement
The angle of plane, and the main rotor shaft of helicopter is generally used the design that leans forward, therefore is generally required before measuring to helicopter
Main rotor shaft carries out " beating vertically ", and need manually when each channel wing setting angle variation checks repeatedly in propeller shank
Position instrument is carved in installation, is all made of this kind of measurement method at present, and the measurement method guarantee condition is more, low efficiency, safety are poor.
Summary of the invention
The purpose of the present invention: to solve the above-mentioned problems, the invention proposes a kind of measurements of helicopter blade established angle
Method is measured blade clamping plate blade mounting surface space angle and center piece space angle respectively, is utilized nothing using sensor technology
Line transmission technology, transmits measurement result to ground based terminal, is resolved by space geometry, finally obtains the blade peace of propeller shank
Angle is filled, once mounting, repeatedly measurement is can be realized, improves guarantee efficiency.
A kind of technical solution of the present invention: measurement method of helicopter blade established angle, comprising the following steps:
Step 1: the ground based terminal of sensor and sensor is connected；
Step 2: being installed sensor by mounting bracket to the benchmark propeller hub of helicopter；
1) first sensor 4 is fixed in the first mounting bracket 3, by blade pin in benchmark propeller hub support arm blade clamping plate
First mounting bracket 3 is installed on 2；
2) second sensor 6 is fixed in the second mounting bracket 5, keeps measuring axis direction unanimously with first sensor 4,
Second mounting bracket 5 is installed in center piece 1 by quick-release spring catch；
Step 3: main blade plays cone inspection in advance；
Collective-pitch lever, control stick, pedal are placed in base position, propeller hub support arm is placed in four different orientations respectively, is led to
The wing setting angle that ground based terminal records measurement respectively is crossed, and is recorded respectively, checks whether main blade taper meets the requirements；
Step 4: carrying out main pitch established angle variation inspection, main paddle longitudinal period respectively after main blade taper is met the requirements
Established angle variation checks, the lateral period established angle variation of main paddle checks；
Preferably, it in the step 4, carries out main pitch established angle variation and checks, by the way that benchmark propeller hub support arm is placed in one
Collective-pitch lever, is placed on low away from, rise position by a azimuth respectively, checks whether main pitch established angle variable quantity meets the requirements.
Preferably, it in the step 4, carries out the longitudinal period established angle variation of main paddle and checks, by by benchmark propeller hub support arm
It is placed in an azimuth, collective-pitch lever is placed on the preceding limit, rear extreme position respectively, checks the longitudinal period established angle variable quantity of main paddle
Whether meet the requirements.
Preferably, it in the step 4, carries out the lateral period established angle variation of main paddle and checks, by by benchmark propeller hub support arm
It is placed in an azimuth, collective-pitch lever is placed on limit on the left, limit on the right-right-hand limit position respectively, checks the lateral period established angle variable quantity of main paddle
Whether meet the requirements.
Preferably, the step 3 wing setting angle is resolved using four azimuthal space angle geometry.
Preferably, in the step 4, blade is placed in four different orientations and is carried out main pitch established angle respectively
Variation checks, the longitudinal period established angle variation of main paddle checks, the lateral period established angle variation of main paddle checks.
Technical effect of the invention: once mounting, repeatedly measurement can be achieved in the present invention, and easy to use, stable accuracy ensures
It is high-efficient, it also can guarantee the personal safety of survey crew, reduce labor intensity.Mounting frame for sensor is changed by adaptability,
The installation interface of change and helicopter, it is subsequent gradually to extend to other type helicopters.
Detailed description of the invention
Fig. 1 is that a kind of sensor installation of a preferred embodiment of the measurement method of helicopter blade established angle of the present invention is shown
It is intended to；
Fig. 2 is a kind of flow diagram of a preferred embodiment of the measurement method of helicopter blade established angle of the present invention；
Wherein, 1- center piece, 2- blade clamping plate, the first mounting bracket of 3-, 4- first sensor, the second mounting bracket of 5-,
6- second sensor.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
The embodiment of the present invention is described in detail with reference to the accompanying drawing, please refers to Fig. 1 to Fig. 2；
A kind of measurement method of Helicopter Main rotor blade established angle, will measurement helicopter vertical state under blade clamping plate and
The angle of horizontal plane is changed to the angle of blade clamping plate 2 and center piece 1 under measurement helicopter orderly closedown state, passes through baseline blade
It is resolved in four azimuthal space angle geometry, realizes the measurement of wing setting angle.
This method includes that the main pitch established angle variation of flight control system checks, the longitudinal period established angle variation of main paddle is examined
It looks into, the lateral period established angle variation of main paddle checks.
Specific step is as follows for this method:
One, main blade beats cone checking step in advance
Step 1: dismantling main blade, first sensor 4 is fixed in the first mounting bracket 3, by blade pin in benchmark
First mounting bracket 3 is installed on propeller hub support arm blade clamping plate 2；
Step 2: second sensor 6 is fixed in the second mounting bracket of sensor 5, keeps measuring with first sensor 4
Axis installs the second mounting bracket of sensor 5 by quick-release spring catch towards unanimously in center piece 1,；
Step 3: being placed in base position for collective-pitch lever, control stick, pedal, and propeller hub support arm is placed in four not Tongfangs respectively
Parallactic angle records the wing setting angle of measurement by ground based terminal respectively；
Step 4: it measures the wing setting angle of remaining blade respectively according to step 1 to three, and records respectively, check main paddle
Whether leaf taper meets the requirements.
Two, main pitch established angle variation checks
Step 1: the first mounting bracket 3 is installed on benchmark propeller hub support arm blade clamping plate 2 by blade pin；
Step 2: the of second sensor is installed by quick-release spring catch on benchmark propeller hub support arm damper lock washer
Two mounting brackets 5；
Step 3: being placed in a certain azimuth for benchmark propeller hub support arm, is respectively placed on collective-pitch lever low away from, rise position, leads to
Cross the main pitch established angle of ground based terminal record measurement；
Step 4: being placed in its excess-three different orientations for benchmark propeller hub support arm respectively, surveys according to step 1 to three records
The main pitch established angle of amount, checks whether main pitch established angle variable quantity meets the requirements.
Three, the longitudinal period established angle of main paddle changes checking step
Step 1: the first mounting bracket 3 is installed on benchmark propeller hub support arm blade clamping plate 2 by blade pin；
Step 2: second sensor is equipped on benchmark propeller hub support arm damper lock washer by quick-release spring catch
Second mounting bracket 5；
Step 3: being placed in a certain azimuth for benchmark propeller hub support arm, and control stick is placed on the preceding limit, rear limit position respectively
It sets, passes through the longitudinal period established angle of main paddle of ground based terminal record measurement；
Step 4: being placed in its excess-three different orientations for benchmark propeller hub support arm respectively, surveys according to step 1 to three records
The longitudinal period established angle of the main paddle of amount, checks whether the longitudinal period established angle variable quantity of main paddle meets the requirements.
Four, the lateral period established angle of main paddle changes checking step
Step 1: the first mounting bracket 3 is installed on benchmark propeller hub support arm blade clamping plate 2 by blade pin；
Step 2: the of second sensor is installed by quick-release spring catch on benchmark propeller hub support arm damper lock washer
Two mounting brackets 5；
Step 3: benchmark propeller hub support arm is placed in a certain azimuth, control stick is placed on limit on the left, limit on the right-right-hand limit position respectively
It sets, passes through the lateral period established angle of main paddle of ground based terminal record measurement；
Step 4: being placed in its excess-three different orientations for benchmark propeller hub support arm respectively, surveys according to step 1 to three records
The lateral period established angle of the main paddle of amount, checks whether the lateral period established angle variable quantity of main paddle meets the requirements.
A kind of measurement method of helicopter blade established angle of the present invention measures blade clamping plate using sensor technology respectively
Blade mounting surface space angle and center piece space angle transmit measurement result to ground based terminal using Radio Transmission Technology,
It is resolved by space geometry, finally obtains the wing setting angle of propeller shank, can be realized once mounting, repeatedly measurement, improve
Guarantee efficiency also can guarantee the personal safety of survey crew, reduce labor intensity.Sensor installation branch is changed by adaptability
Frame, the installation interface of change and helicopter are subsequent gradually to extend to other type helicopters.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (5)
1. a kind of measurement method of helicopter blade established angle, it is characterised in that: the following steps are included:
Step 1: the ground based terminal of sensor and sensor is connected；
Step 2: being installed sensor by mounting bracket to the benchmark propeller hub of helicopter；
1) first sensor 4 is fixed in the first mounting bracket 3, through blade pin on benchmark propeller hub support arm blade clamping plate 2
First mounting bracket 3 is installed；
2) second sensor 6 is fixed in the second mounting bracket 5, keeps measuring axis with first sensor 4 towards unanimously, passes through
Quick-release spring catch installs the second mounting bracket 5 in center piece 1；
Step 3: main blade plays cone inspection in advance；
Collective-pitch lever, control stick, pedal are placed in base position, propeller hub support arm is placed in four different orientations respectively, passes through ground
Face terminal records the wing setting angle of measurement respectively, and records respectively, checks whether main blade taper meets the requirements, wherein slurry
Leaf established angle is resolved using four azimuthal space angle geometry；
Step 4: carrying out main pitch established angle variation inspection, the longitudinal period installation of main paddle respectively after main paddle taper is met the requirements
Angle variation checks, the lateral period established angle variation of main paddle checks.
2. a kind of measurement method of helicopter blade established angle according to claim 1, it is characterised in that: the step 4
In, it carries out main pitch established angle variation and checks, by the way that benchmark propeller hub support arm is placed in an azimuth, be respectively placed on collective-pitch lever
It is low away from, rise position, check whether main pitch established angle variable quantity meets the requirements.
3. a kind of measurement method of helicopter blade established angle according to claim 1, it is characterised in that: the step 4
In, carry out the longitudinal period established angle variation of main paddle and check, by the way that benchmark propeller hub support arm is placed in an azimuth, respectively will always away from
Bar is placed on the preceding limit, rear extreme position, checks whether the longitudinal period established angle variable quantity of main paddle meets the requirements.
4. a kind of measurement method of helicopter blade established angle according to claim 1, it is characterised in that: the step 4
In, carry out the lateral period established angle variation of main paddle and check, by the way that benchmark propeller hub support arm is placed in an azimuth, respectively will always away from
Bar is placed on limit on the left, limit on the right-right-hand limit position, checks whether the lateral period established angle variable quantity of main paddle meets the requirements.
5. a kind of measurement method of helicopter blade established angle according to claim 1, it is characterised in that: the step 4
In, paddle is placed in four different orientations and is carried out main pitch established angle variation inspection, the longitudinal period installation of main paddle respectively
Angle variation checks, the lateral period established angle variation of main paddle checks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201611075469.7A CN106767651B (en) | 2016-11-29 | 2016-11-29 | A kind of measurement method of helicopter blade established angle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611075469.7A CN106767651B (en) | 2016-11-29 | 2016-11-29 | A kind of measurement method of helicopter blade established angle |
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| CN106767651A CN106767651A (en) | 2017-05-31 |
| CN106767651B true CN106767651B (en) | 2019-05-31 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533390B (en) * | 2018-11-15 | 2020-11-03 | 中国直升机设计研究所 | Support for measuring mounting angle of propeller hub support arm |
| CN111099038B (en) * | 2019-12-19 | 2021-06-01 | 武汉航空仪表有限责任公司 | Helicopter main blade azimuth angle detection device |
| CN112373721B (en) * | 2020-11-03 | 2023-02-10 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting reference of main-rotor steering engine of helicopter in ground state |
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| CN101376433A (en) * | 2008-10-10 | 2009-03-04 | 南京航空航天大学 | Helicopter rotor operation method and system |
| CN201307004Y (en) * | 2008-12-11 | 2009-09-09 | 中国航空工业第六〇二研究所 | A helicopter airscrew propeller pitch angle dynamic calibration system |
| CN103900811A (en) * | 2012-12-25 | 2014-07-02 | 中国直升机设计研究所 | Rotation load applying device for tail rotor shaft fatigue test |
| CN205228397U (en) * | 2015-11-26 | 2016-05-11 | 广州航新航空科技股份有限公司 | Rotor centrum monitoring devices |
| CN105841948A (en) * | 2016-05-16 | 2016-08-10 | 宁波星箭航天机械有限公司 | Helicopter rotor hub bridle test board and test method therefor |
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2016
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB923232A (en) * | 1958-04-23 | 1963-04-10 | Chicago Aerial Ind Inc | Parallax interval sensing device |
| CN101376433A (en) * | 2008-10-10 | 2009-03-04 | 南京航空航天大学 | Helicopter rotor operation method and system |
| CN201307004Y (en) * | 2008-12-11 | 2009-09-09 | 中国航空工业第六〇二研究所 | A helicopter airscrew propeller pitch angle dynamic calibration system |
| CN103900811A (en) * | 2012-12-25 | 2014-07-02 | 中国直升机设计研究所 | Rotation load applying device for tail rotor shaft fatigue test |
| CN205228397U (en) * | 2015-11-26 | 2016-05-11 | 广州航新航空科技股份有限公司 | Rotor centrum monitoring devices |
| CN105841948A (en) * | 2016-05-16 | 2016-08-10 | 宁波星箭航天机械有限公司 | Helicopter rotor hub bridle test board and test method therefor |
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