CN106767651A - A kind of measuring method of helicopter blade established angle - Google Patents
A kind of measuring method of helicopter blade established angle Download PDFInfo
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- CN106767651A CN106767651A CN201611075469.7A CN201611075469A CN106767651A CN 106767651 A CN106767651 A CN 106767651A CN 201611075469 A CN201611075469 A CN 201611075469A CN 106767651 A CN106767651 A CN 106767651A
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- established angle
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- blade
- sensor
- mounting bracket
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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
Abstract
The invention discloses a kind of measuring method of helicopter blade established angle, belong to helicopter technical field of measurement and test.Comprise the following steps：Step one, sensor is connected with the ground based terminal of sensor；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, is kept with first sensor measurement axle towards consistent, by installing the second mounting bracket in center piece；Step 3, collective-pitch lever, control stick, pedal are placed in reference position, propeller hub support arm is placed in four different orientations respectively, record the wing setting angle of measurement respectively by ground based terminal, check whether main blade taper meets requirement；After step 4, main blade taper meet and require, carry out that the change of main pitch established angle is checked, the cycle established angle change of main oar longitudinal direction is checked, the established angle change of main oar transverse direction cycle is checked respectively.The present invention can realize once mounting, repeatedly measurement, improve guarantee efficiency.
Description
Technical field
The invention belongs to helicopter technical field of measurement and test, and in particular to a kind of measuring method of helicopter blade established angle.
Background technology
Part (such as booster, steering wheel) is installed or changed to helicopter flight steerable system afterwards, it is necessary to system on machine
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, its degree of accuracy is directly connected to the flying quality of helicopter
And flight quality.
Traditional wing setting angle measurement measures the wing setting angle of propeller shank by it generally using the measurement of position instrument is carved
Judge whether to meet flight control system design requirement with the angle of horizontal plane, its principle carves position instrument mounting surface and water for measurement
The angle of plane, and the main rotor shaft of helicopter typically all uses the design that leans forward, therefore generally require before measuring to helicopter
Main rotor shaft is carried out " beating vertical ", and needed manually repeatedly in propeller shank when each passage wing setting angle change is checked
Install and carve position instrument, this kind of metering system is used at present, the measuring method guarantee condition is more, efficiency is low, security is poor.
The content of the invention
The purpose of the present invention：In order to solve the above problems, the present invention proposes a kind of measurement of helicopter blade established angle
Method, using sensor technology, measures blade clamping plate blade mounting surface space angle and center piece space angle, using nothing respectively
Line transmission technology, transmits measurement result to ground based terminal, is resolved by space geometry, finally gives the blade peace of propeller shank
Dress angle, can realize once mounting, repeatedly measurement, improve guarantee efficiency.
Technical scheme：A kind of measuring method of helicopter blade established angle, comprises the following steps：
Step one, sensor is connected with the ground based terminal of sensor；
Step 2, sensor is attached on the benchmark propeller hub of helicopter by mounting bracket；
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 consistent with the measurement axle direction of first sensor 4,
Second mounting bracket 5 is installed in center piece 1 by quick-release spring catch；
Step 3, main blade play cone inspection in advance；
Collective-pitch lever, control stick, pedal are placed in reference position, propeller hub support arm is placed in four different orientations respectively, led to
Cross ground based terminal and record the wing setting angle of measurement respectively, and record respectively, check whether main blade taper meets requirement；
After step 4, main blade taper meet requirement, main pitch established angle change inspection, main oar longitudinal direction cycle are carried out respectively
Established angle change is checked, the established angle change of main oar transverse direction cycle is checked；
Preferably, in the step 4, carry out main pitch established angle change and check, one is placed in by by benchmark propeller hub support arm
, be placed on for collective-pitch lever respectively low away from, rise position by individual azimuth, checks whether main pitch established angle variable quantity meets requirement.
Preferably, in the step 4, carry out the cycle established angle change of main oar longitudinal direction and check, by by benchmark propeller hub support arm
An azimuth is placed in, collective-pitch lever is placed on the preceding limit, rear extreme position respectively, check main oar longitudinal direction cycle established angle variable quantity
Whether satisfaction is required.
Preferably, in the step 4, carry out the established angle change of main oar transverse direction cycle and check, by by benchmark propeller hub support arm
An azimuth is placed in, collective-pitch lever is placed on limit on the left, limit on the right-right-hand limit position respectively, check main oar transverse direction cycle established angle variable quantity
Whether satisfaction is required.
Preferably, the step 3 wing setting angle is resolved using four azimuthal space angle geometry.
Preferably, in the step 4, blade is placed in into four different orientations is carried out main pitch established angle respectively
Change is checked, the cycle established angle change of main oar longitudinal direction is checked, the established angle change of main oar transverse direction cycle is checked.
Technique effect of the invention：The achievable once mounting of the present invention, repeatedly measurement, easy to use, stable accuracy are ensured
Efficiency high, can also ensure the personal safety of survey crew, reduce labour intensity.Mounting frame for sensor is changed by adaptability,
Change and the mounting interface of helicopter, subsequently can progressively extend to other type helicopters.
Brief description of the drawings
Fig. 1 is that a kind of sensor installation of a preferred embodiment of the measuring method of helicopter blade established angle of the invention is shown
It is intended to；
Fig. 2 is a kind of schematic flow sheet of a preferred embodiment of the measuring method of helicopter blade established angle of the invention；
Wherein, 1- center pieces, 2- blade clamping plates, the mounting brackets of 3- first, 4- first sensors, the mounting brackets of 5- second,
6- second sensors.
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Face is described in detail with reference to accompanying drawing to embodiments of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of the description present invention and simplify description, rather than the dress for indicating or implying meaning
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The limitation of scope.
Embodiments of the invention are described in detail below in conjunction with the accompanying drawings, refer to Fig. 1 to Fig. 2；
A kind of measuring 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, by baseline blade
Resolved in four azimuthal space angle geometry, realize the measurement of wing setting angle.
The method includes that the main pitch established angle change of flight control system is checked, main oar longitudinal direction cycle established angle changes inspection
Look into, the established angle change of main oar transverse direction cycle is checked.
The method is comprised the following steps that：
First, main blade beats cone checking step in advance
Step one：Main blade is dismantled, 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, holding is measured with first sensor 4
Axle towards consistent, by quick-release spring catch in center piece 1 the second mounting bracket of install sensor 5,；
Step 3：Collective-pitch lever, control stick, pedal are placed in reference position, propeller hub support arm is placed in four not Tongfangs respectively
Parallactic angle, the wing setting angle of measurement is recorded by ground based terminal respectively；
Step 4：Measure the wing setting angle of remaining blade respectively according to step one to three, and record respectively, check main oar
Whether leaf taper meets requirement.
2nd, main pitch established angle change is checked
Step one：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 on benchmark propeller hub support arm damper lock washer by quick-release spring catch
Two mounting brackets 5；
Step 3：Benchmark propeller hub support arm is placed in a certain azimuth, is respectively placed on collective-pitch lever low away from, rise position, led to
Cross the main pitch established angle of ground based terminal record measurement；
Step 4：Benchmark propeller hub support arm is placed in its excess-three different orientations respectively, is surveyed according to step one to three records
The main pitch established angle of amount, checks whether main pitch established angle variable quantity meets requirement.
3rd, main oar longitudinal direction cycle established angle change checking step
Step one：First mounting bracket 3 is installed on benchmark propeller hub support arm blade clamping plate 2 by blade pin；
Step 2：Second sensor is provided with benchmark propeller hub support arm damper lock washer by quick-release spring catch
Second mounting bracket 5；
Step 3：Benchmark propeller hub support arm is placed in a certain azimuth, control stick is placed on the preceding limit, rear limit position respectively
Put, the main oar longitudinal direction cycle established angle of measurement is recorded by ground based terminal；
Step 4：Benchmark propeller hub support arm is placed in its excess-three different orientations respectively, is surveyed according to step one to three records
The main oar longitudinal direction cycle established angle of amount, checks whether main oar longitudinal direction cycle established angle variable quantity meets requirement.
4th, main oar transverse direction cycle established angle change checking step
Step one：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 on benchmark propeller hub support arm damper lock washer by quick-release spring catch
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
Put, the main oar transverse direction cycle established angle of measurement is recorded by ground based terminal；
Step 4：Benchmark propeller hub support arm is placed in its excess-three different orientations respectively, is surveyed according to step one to three records
The main oar transverse direction cycle established angle of amount, checks whether main oar transverse direction cycle established angle variable quantity meets requirement.
A kind of measuring method of helicopter blade established angle of the present invention, using sensor technology, measures blade clamping plate respectively
Blade mounting surface space angle and center piece space angle, using Radio Transmission Technology, transmit measurement result to ground based terminal,
Resolved by space geometry, finally give the wing setting angle of propeller shank, once mounting, repeatedly measurement can be realized, improved
Guarantee efficiency, can also ensure the personal safety of survey crew, reduce labour intensity.Sensor is changed by adaptability branch is installed
Frame, change and the mounting interface of helicopter, subsequently can progressively extend to other type helicopters.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, do not make the essence of the essence disengaging various embodiments of the present invention technical scheme of appropriate technical solution
God and scope.
Claims (6)
1. a kind of measuring method of helicopter blade established angle, it is characterised in that：Comprise the following steps：
Step one, sensor is connected with the ground based terminal of sensor；
Step 2, sensor is attached on the benchmark propeller hub of helicopter by mounting bracket；
1) first sensor 4 is fixed in the first mounting bracket 3, by 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, is kept with the measurement axle of first sensor 4 towards consistent, passed through
Quick-release spring catch installs the second mounting bracket 5 in center piece 1；
Step 3, main blade play cone inspection in advance；
Collective-pitch lever, control stick, pedal are placed in reference position, propeller hub support arm four different orientations is placed in respectively, by ground
Face terminal records the wing setting angle of measurement respectively, and records respectively, checks whether main blade taper meets requirement；
After step 4, main blade taper meet requirement, main pitch established angle change inspection, main oar longitudinal direction cycle are carried out respectively and is installed
Angle change is checked, the established angle change of main oar transverse direction cycle is checked.
2. the measuring method of a kind of helicopter blade established angle according to claim 1, it is characterised in that:The step 4
In, carry out main pitch established angle change and check, an azimuth is placed in by by benchmark propeller hub support arm, collective-pitch lever is placed on respectively
It is low away from, rise position, check whether main pitch established angle variable quantity meets requirement.
3. the measuring method of a kind of helicopter blade established angle according to claim 1, it is characterised in that:The step 4
In, carry out the cycle established angle change of main oar longitudinal direction and check, be placed in an azimuth by by benchmark propeller hub support arm, respectively will always away from
Bar is placed on the preceding limit, rear extreme position, checks whether main oar longitudinal direction cycle established angle variable quantity meets requirement.
4. the measuring method of a kind of helicopter blade established angle according to claim 1, it is characterised in that:The step 4
In, carry out the established angle change of main oar transverse direction cycle and check, be placed in an azimuth by by benchmark propeller hub support arm, respectively will always away from
Bar is placed on limit on the left, limit on the right-right-hand limit position, checks whether main oar transverse direction cycle established angle variable quantity meets requirement.
5. the measuring method of a kind of helicopter blade established angle according to claim 1, it is characterised in that:The step 3
Wing setting angle is resolved using four azimuthal space angle geometry.
6. the measuring method of a kind of helicopter blade established angle according to claim 1, it is characterised in that:The step 4
In, blade is placed in into four different orientations is carried out main pitch established angle change inspection, the cycle installation of main oar longitudinal direction respectively
Angle change is checked, the established angle change of main oar transverse direction cycle is checked.
Priority Applications (1)
| 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 |
Applications Claiming Priority (1)
| 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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| Publication Number | Publication Date |
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| CN106767651A true CN106767651A (en) | 2017-05-31 |
| CN106767651B CN106767651B (en) | 2019-05-31 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533390A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of bracket for propeller hub support arm installation angular measurement |
| CN111099038A (en) * | 2019-12-19 | 2020-05-05 | 武汉航空仪表有限责任公司 | Helicopter main blade azimuth angle detection device |
| CN112373721A (en) * | 2020-11-03 | 2021-02-19 | 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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| 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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Patent Citations (6)
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| 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 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533390A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of bracket for propeller hub support arm installation angular measurement |
| 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 |
| CN111099038A (en) * | 2019-12-19 | 2020-05-05 | 武汉航空仪表有限责任公司 | Helicopter main blade azimuth angle detection device |
| 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 |
| CN112373721A (en) * | 2020-11-03 | 2021-02-19 | 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 |
| 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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| Publication number | Publication date |
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| CN106767651B (en) | 2019-05-31 |
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