CN109238231A - A kind of aircraft rudder surface angle measurement unit and its measurement method - Google Patents
A kind of aircraft rudder surface angle measurement unit and its measurement method Download PDFInfo
- Publication number
- CN109238231A CN109238231A CN201810939697.7A CN201810939697A CN109238231A CN 109238231 A CN109238231 A CN 109238231A CN 201810939697 A CN201810939697 A CN 201810939697A CN 109238231 A CN109238231 A CN 109238231A
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- CN
- China
- Prior art keywords
- sucker
- bracket
- gradient measurer
- measurement unit
- measurement
- Prior art date
- 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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C9/00—Measuring inclination, e.g. by clinometers, by levels
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C9/00—Measuring inclination, e.g. by clinometers, by levels
- G01C9/02—Details
Abstract
The present invention relates to a kind of aircraft rudder surface angle measurement unit and its measurement methods, the gradient measurer that its device includes bracket, is arranged on bracket, it further include the sucker for cooperating gradient measurer and rudder face, the upper end of the sucker is provided with rocker arm, the lower end of the sucker is provided with the connector with support assorted, it is provided between the bracket and connector convenient for the universal shaft of gradient measurer rotation measuring, specific step is as follows for measurement method: (1) fixed；(2) horizontality；(3) it resets；(4) operating angle；(5) measurement terminates；With the measurement method of the original mechanical protractor measurement control surface deflection angle of the gradient measurer substitution of electrical type, the present invention can be realized the variable quantity of digital display real-time display control surface deflection angle, advantage compared to mechanical protractor is display precision height, reduce artificial error in reading, reduce error, precision is high, easily operated.
Description
Technical field
The present invention relates to technical field of angle detection, specifically a kind of aircraft rudder surface angle measurement unit and its measurement side
Method.
Background technique
Known rudder face angle measurement method, mainly by means of mechanical goniometer be placed in deflection rudder face on, pointer by
In gravity, always vertically downward, when deflecting rudder face, the angle of throw of pointer is control surface deflection angle, but mechanical
The measuring principle basis of protractor is when reading angular, to need to wait for read after angle indicator is stablized using plumb line principle,
Working efficiency is low, and artificial reading is easy to appear error；Old-fashioned rudder face angle measurement unit is fixed simultaneously controls fixture using screw rod
Firmness be fixed, troublesome in poeration and fixed effect is poor.
Summary of the invention
To solve the above-mentioned problems, the present invention proposes a kind of aircraft rudder surface angle measurement unit and its measurement method.
A kind of aircraft rudder surface angle measurement unit further includes being used for including bracket, the gradient measurer being arranged on bracket
So that the sucker of gradient measurer and rudder face cooperation, the upper end of the sucker are provided with rocker arm, the lower end of the sucker is set
It is equipped with the connector with support assorted, is provided between the bracket and connector convenient for the universal of gradient measurer rotation measuring
Axis.
The bracket is L-type plate, and the gradient measurer is by magnetic-adsorption on bracket.
The gradient measurer is electron type.
The bracket is cooperated by rigid connection and universal shaft.
The rigid connection is flanged joint or welding.
A kind of measurement method of aircraft rudder surface angle measurement unit, the specific steps of which are as follows:
(1) fixation: by gradient measurer by magnetic-adsorption on bracket, bracket, in universal shaft, is incited somebody to action by rigid connection
Sucker 1 is attached on rudder face to be measured；
(2) horizontality: when rocker arm is placed in horizontality, gradient measurer is fixed by vacuum pressure fastness；
(3) reset: when rudder face is in initial position, " Zero " button for pressing gradient measurer is reset；
(4) operating angle: when control surface deflection to operating angle, the deflection of the form real-time display rudder face of gradient measurer
Angle.
(5) measurement terminates: after measurement, rocker arm being placed in position vertically upward, air is filled in sucker and makes
Affranchise state, removes sucker using rocker arm when sucker and rudder face to be measured are in non-tight state.
It needs the air in sucker to be discharged so that sucker and rudder face to be measured are in vacuum abutted shape in the step (1)
State.
The beneficial effects of the present invention are: inclined with the original mechanical protractor measurement rudder face of the gradient measurer substitution of electrical type
The measurement method of gyration, the present invention can be realized the variable quantity of digital display real-time display control surface deflection angle, compared to mechanical angulation
The advantage of device is display precision height, reduces artificial error in reading, reduces error；Simultaneously because mechanical goniometer measuring principle base
Plinth is when reading angular, to need to wait for read after angle indicator is stablized using plumb line principle, and the slope measuring of electrical type
Instrument can have timeliness with real-time measurement angle；Old-fashioned rudder face angle measurement unit is fixed to utilize the secured of screw rod control fixture
Degree, and sucking disk type supporting stand is directly fixed using negative pressure of vacuum principle, keeps the dismounting of rudder face angle measurement unit lighter, fast
Victory improves work efficiency；Fixed cumbersome, the poor universality of original measurement method tooling is overcome, angle-measurement accuracy is not high
Problem improves measurement result and reads intuitive, convenient, precision height, easily operated.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and examples.
Fig. 1 is schematic perspective view of the invention.
Specific embodiment
In order to be easy to understand the technical means, the creative features, the aims and the efficiencies achieved by the present invention, below it is right
The present invention is further described.
As shown in Figure 1, a kind of aircraft rudder surface angle measurement unit, including bracket 2, the slope measuring being arranged on bracket 2
Instrument 3 further includes the sucker 1 for cooperating gradient measurer 3 and rudder face, and the upper end of the sucker 1 is provided with rocker arm
101, the lower end of the sucker 1 is provided with the connector 102 cooperated with bracket 2, is arranged between the bracket 2 and connector 102
There is the universal shaft 103 convenient for 3 rotation measuring of gradient measurer.
The measurement method of original mechanical protractor measurement control surface deflection angle is substituted with the gradient measurer 3 of electrical type,
The present invention can be realized the variable quantity of digital display real-time display control surface deflection angle, and the advantage compared to mechanical protractor is display precision
Height reduces artificial error in reading, reduces error.
The bracket 2 is L-type plate, and the gradient measurer 3 is by magnetic-adsorption on bracket 2.
The gradient measurer 3 is electron type.
The rocker arm 101 is for removing sucker 1.
Since mechanical goniometer measuring principle basis when reading angular, is needed to wait for angle and refers to using plumb line principle
Needle can be read after stablizing, and the gradient measurer 3 of electrical type can have timeliness with real-time measurement angle.
The bracket 2 is cooperated by rigid connection and universal shaft 103.
It is cumbersome to overcome the fixation of original measurement method tooling, the problems such as poor universality, angle-measurement accuracy is not high, improves
It is intuitive, convenient that measurement result is read, and precision is high, easily operated.
The rigid connection is flanged joint or welding.
The fixed firmness using screw rod control fixture of old-fashioned rudder face angle measurement unit, and sucking disk type supporting stand 2 is direct
It is fixed using negative pressure of vacuum principle, keeps the dismounting of rudder face angle measurement unit lighter, quick, improve work efficiency.
A kind of measurement method of aircraft rudder surface angle measurement unit, the specific steps of which are as follows:
(1) fixed: by gradient measurer 3 by magnetic-adsorption on bracket 2, bracket 2 is by rigid connection in universal shaft
103, sucker 1 is attached on rudder face to be measured；
(2) horizontality: when rocker arm 101 is placed in horizontality, gradient measurer 3 is fixed by vacuum pressure fastness；
(3) reset: when rudder face is in initial position, " Zero " button of pressing gradient measurer 3 is reset；
(4) operating angle: when control surface deflection to operating angle, the form real-time display rudder face of gradient measurer 3 it is inclined
Gyration.
(5) measurement terminates: after measurement, rocker arm 101 being placed in position vertically upward, is filled with air in sucker 1
So that removing sucker 1 using rocker arm 101 when the state that affranchises, sucker 1 and rudder face to be measured are in non-tight state.
It needs for the air in sucker 1 to be discharged in the step (1) so that sucker 1 is in vacuum abutted with rudder face to be measured
State.
The basic principles, main features and advantages of the present invention have been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and what is described in the above embodiment and the description is only the present invention
Principle, without departing from the spirit and scope of the present invention, various changes and improvements may be made to the invention, these variation and
Improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention is by appended claims and its equivalent
Object defines.
Claims (6)
1. a kind of aircraft rudder surface angle measurement unit, the gradient measurer (3) including bracket (2), setting on bracket (2),
It is characterized in that: further including for so that the sucker (1) that gradient measurer (3) and rudder face cooperate, the upper end of the sucker (1) is set
It is equipped with rocker arm (101), the lower end of the sucker (1) is provided with the connector (102) with bracket (2) cooperation, the bracket (2)
It is provided between connector (102) convenient for the universal shaft (103) of gradient measurer (3) rotation measuring.
2. a kind of aircraft rudder surface angle measurement unit according to claim 1, it is characterised in that: the bracket (2) is L
Template, for the gradient measurer (3) through magnetic-adsorption on bracket (2), the gradient measurer (3) is electron type.
3. a kind of aircraft rudder surface angle measurement unit according to claim 1, it is characterised in that: the bracket (2) is logical
It crosses rigid connection and universal shaft (103) cooperates.
4. a kind of aircraft rudder surface angle measurement unit according to claim 3, it is characterised in that: the rigid connection is
Flanged joint or welding.
5. using a kind of measurement method of aircraft rudder surface angle measurement unit described in any one of any one of claims 1 to 44, feature
It is: the specific steps of which are as follows:
(1) fixed: by gradient measurer (3) by magnetic-adsorption on bracket (2), bracket (2) is by rigid connection in universal
Sucker (1) is attached on rudder face to be measured by axis (103)；
(2) horizontality: when rocker arm (101) is placed in horizontality, gradient measurer (3) is fixed by vacuum pressure fastness；
(3) reset: when rudder face is in initial position, " Zero " button of pressing gradient measurer (3) is reset；
(4) operating angle: when control surface deflection to operating angle, the deflection of the form real-time display rudder face of gradient measurer (3)
Angle；
(5) measurement terminates: after measurement, rocker arm (101) being placed in position vertically upward, is filled with air in sucker (1)
So that removing sucker (1) using rocker arm (101) when the state that affranchises, sucker (1) and rudder face to be measured are in non-tight state.
6. a kind of measurement method of aircraft rudder surface angle measurement unit according to claim 5, it is characterised in that: it is described
It needs the air in sucker (1) to be discharged so that sucker (1) and rudder face to be measured are in vacuum abutted state in step (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810939697.7A CN109238231A (en) | 2018-08-17 | 2018-08-17 | A kind of aircraft rudder surface angle measurement unit and its measurement method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810939697.7A CN109238231A (en) | 2018-08-17 | 2018-08-17 | A kind of aircraft rudder surface angle measurement unit and its measurement method |
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| Publication Number | Publication Date |
|---|---|
| CN109238231A true CN109238231A (en) | 2019-01-18 |
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ID=65070069
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810939697.7A Pending CN109238231A (en) | 2018-08-17 | 2018-08-17 | A kind of aircraft rudder surface angle measurement unit and its measurement method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110345902A (en) * | 2019-07-16 | 2019-10-18 | 北京普利永华科技发展有限公司 | A method of testing rudder face corner under aircraft not horizontality |
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|---|---|---|---|---|
| JPH07112699A (en) * | 1993-10-18 | 1995-05-02 | Daisuke Shimomoto | Meandering preventing method by automatic pilot |
| CN203956863U (en) * | 2014-06-24 | 2014-11-26 | 嘉善威尔尼绒业有限公司 | A kind of repair apparatus |
| CN104512351A (en) * | 2014-11-26 | 2015-04-15 | 重庆长野汽车配件有限公司 | Suction fixing and magnetic fixing combined vehicle navigation instrument |
| CN205173926U (en) * | 2015-12-07 | 2016-04-20 | 重庆工业职业技术学院 | Camera mount that can adsorb location on wet and slippery wall of stereoplasm |
| CN205260583U (en) * | 2015-12-21 | 2016-05-25 | 王江飞 | Powerful magnetism mounting |
| CN108168498A (en) * | 2018-02-06 | 2018-06-15 | 中国航天空气动力技术研究院 | A kind of Portable aircraft aerofoil corner measuring apparatus |
-
2018
- 2018-08-17 CN CN201810939697.7A patent/CN109238231A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07112699A (en) * | 1993-10-18 | 1995-05-02 | Daisuke Shimomoto | Meandering preventing method by automatic pilot |
| CN203956863U (en) * | 2014-06-24 | 2014-11-26 | 嘉善威尔尼绒业有限公司 | A kind of repair apparatus |
| CN104512351A (en) * | 2014-11-26 | 2015-04-15 | 重庆长野汽车配件有限公司 | Suction fixing and magnetic fixing combined vehicle navigation instrument |
| CN205173926U (en) * | 2015-12-07 | 2016-04-20 | 重庆工业职业技术学院 | Camera mount that can adsorb location on wet and slippery wall of stereoplasm |
| CN205260583U (en) * | 2015-12-21 | 2016-05-25 | 王江飞 | Powerful magnetism mounting |
| CN108168498A (en) * | 2018-02-06 | 2018-06-15 | 中国航天空气动力技术研究院 | A kind of Portable aircraft aerofoil corner measuring apparatus |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110345902A (en) * | 2019-07-16 | 2019-10-18 | 北京普利永华科技发展有限公司 | A method of testing rudder face corner under aircraft not horizontality |
| CN110345902B (en) * | 2019-07-16 | 2021-07-09 | 北京普利永华科技发展有限公司 | Method for testing control surface corner in non-horizontal state of airplane |
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Application publication date: 20190118 |
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