CN208398849U - A kind of cracking rudder face degree of bias measuring device based on gravity - Google Patents
A kind of cracking rudder face degree of bias measuring device based on gravity Download PDFInfo
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- CN208398849U CN208398849U CN201820183973.7U CN201820183973U CN208398849U CN 208398849 U CN208398849 U CN 208398849U CN 201820183973 U CN201820183973 U CN 201820183973U CN 208398849 U CN208398849 U CN 208398849U
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- rudder face
- cracking
- measuring device
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Abstract
The cracking rudder face degree of bias measuring device based on gravity that the utility model relates to a kind of comprising: base support, base support include pedestal and the bracket that connect with pedestal integral type；Dial, dial are arranged to the sector structure with lightening hole, and the center of circle of dial and bracket are fixed far from one end of pedestal and the center line of dial is overlapped with bracket middle line, and are equipped with graduation mark along the arc edge of sector structure；Vernier pointer, vernier pointer one end is rotatably set to dial the center point, the vernier pointer other end is arranged to the measurement portion with certain area, there can be vernier graduation in measurement portion, vernier graduation and graduation mark cooperate to measure deflection angle of the vernier pointer relative to dial center line.The utility model is during measuring rudder face, using gravity as references object, by setting the scale of different accuracy in dial and measurement portion mark, can accurately measure the deflection angle of rudder face, has many advantages, such as that structure is simple and convenient to operate.
Description
Technical field
The utility model belongs to field of measuring technique more particularly to a kind of cracking rudder face degree of bias based on gravity is surveyed
Measure device.
Background technique
Aircraft rudder surface is steerable airfoil portion on aircraft wing, and rudder face can realize aircraft liter by deflecting certain angle
The change of power or posture.
It during airplane design, needs to measure the deflection angle of rudder face, to grasp the deflection capacity of rudder face.
Therefore a kind of measuring device is needed, the deflection angle of rudder face can be accurately measured.
Utility model content
The cracking rudder face degree of bias measuring device based on gravity that the purpose of the utility model is to provide a kind of, for solving
The certainly above problem.
In order to achieve the above objectives, the technical solution adopted in the utility model is: a kind of cracking rudder based on gravity
Deflecting facet measuring device, the cracking rudder face measuring device include
Base support, base support include pedestal and the bracket that connect with pedestal integral type；
Dial, dial are arranged to the sector structure with lightening hole, and the center of circle of dial and bracket are far from pedestal
One end is fixed and the center line of dial is overlapped with the bracket middle line, and is equipped with scale along the arc edge of sector structure
Line；
Vernier pointer, described vernier pointer one end is rotatably set to dial the center point, the vernier pointer other end is set
It is set to the measurement portion with certain area, there can be vernier graduation in measurement portion, vernier graduation and graduation mark cooperate to measure vernier
Deflection angle of the pointer relative to dial center line.
In the above scheme, the pedestal quadrangle is equipped with adjustable feet, and adjustable feet is used for adjustment base height.
In the above scheme, the angle of the sector structure is not less than 130 degree, so that every side of dial is from radius to quarter
The angle of scale center line is not less than 65 degree.
In the above scheme, the scale value of the dial is 1 degree, and the vernier graduation value of the measurement portion is 5.5 degree.
In the above scheme, the graduation mark and vernier graduation are directed to the sector structure center of circle.
The cracking rudder face degree of bias measuring device based on gravity of the utility model is during measuring rudder face, with weight
Power is references object, by setting the scale of different accuracy in dial and measurement portion mark, can accurately measure the deflection angle of rudder face,
It has many advantages, such as that structure is simple and convenient to operate.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows and meets the utility model
Embodiment, and be used to explain the principles of the present invention together with specification.
Fig. 1 is that the cracking rudder face degree of bias measuring device of the utility model forms figure.
Fig. 2 is the measuring device schematic diagram figure of the utility model.
Fig. 3 is the cracking rudder face degree of bias measuring device installation diagram of the utility model.
Specific embodiment
To keep the purposes, technical schemes and advantages of the utility model implementation clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.
As Fig. 1 to Fig. 3 is devised a kind of based on gravity to measure the deflection angle of rudder face in the utility model
Cracking control surface deflection measuring device, the cracking rudder face measuring device in the utility model specifically includes base support 1, carves
Scale 2 and vernier pointer 3.
Base support 1 is made of pedestal 11 and the bracket 12 connecting with 11 integral type of pedestal, and pedestal 11 is general rectangular,
The part that 12 lower part of bracket is connect with pedestal 11 is rectangle, and bracket 12 extends most end form from its bottom to the part far from pedestal 11
At one similar to pyramidal structure, for supporting dial 2.
Dial 2 is to be arranged to the sector structure with lightening hole, and the center of circle of dial 2 and bracket 12 are far from pedestal 11
One end is fixed, and the fan shape center line of dial 2 is overlapped with the structure middle line of bracket 12, in the arc edge along sector structure
Measurement equipped with graduation mark, for angle.
One end of vernier pointer 3 is rotatably set to the center point of dial 2, and the other end of vernier pointer 3 is arranged to
Measurement portion 31 with certain area can have vernier graduation in measurement portion 31, and the graduation mark on vernier graduation and dial 2 cooperates
To measure deflection angle of the vernier pointer 3 relative to 2 center line of dial (gravity).
In Fig. 1, the quadrangle of pedestal 11 is equipped with adjustable feet 111 in the present invention, and adjustable feet 11 can be used for
The height at 11 4 angles of adjustment base guarantees the smooth rotation of vernier pointer 3 at shaft so that pedestal 11 is parallel with rudder face.This
Outside, adjustable feet 111 can be made of anti-slip material, when base support 1 to be placed on deflectable rudder face, prevent from cracking
The opposite sliding of formula rudder face measuring device and rudder face.
In the utility model embodiment, in order to guarantee the measurement to control surface deflection angular range, by the angle of sector structure
Degree is arranged to be not less than 130 degree, may make the angle from fan-shaped radius to dial center line of the every side of dial 2 so not
Lower than 65 degree.
In the utility model embodiment, in order to guarantee the precision to control surface deflection angle measurement, by the scale of dial 2
Value is 1 degree, and the vernier graduation value of measurement portion 11 is 5.5 degree, and specific measurement method can refer to hereafter.Wherein, the scale of dial 2
Line and vernier graduation are directed to the sector structure center of circle, so that in vernier pointer 3, when being rotated with the center of circle, two scales can be with closing.
When measuring rudder face 4 with respect to deflection angle, need to look for a reference, the measuring device of the utility model is to choose weight
As reference, vernier pointer 3 points to the earth's core forever in power direction, and original state adjusts 0 ° of groove weight of dial 2 and vernier pointer 3
It closes, measurement portion 31 is rotated with rudder face 4, and measuring device schematic diagram is shown in Fig. 2, and ∠ A ' is control surface deflection angle, according to right angle trigonometry
Shape correspondence theorem can deduce that ∠ A '=∠ A, ∠ A degree is the signified reading of vernier pointer 3, to measure the relatively inclined of rudder face
Gyration.
In order to realize that vernier pointer 3 is directed toward the earth's core and dial 2 follows rudder face 4 to rotate this function, vernier pointer 3
Connection between bracket 12 is designed to smooth steel ball connection, so that vernier pointer 3 is naturally drooped direction by gravity
The earth's core；Dial 2 compresses it with bracket 12 after zeroing, with clamping screw, and base support 1 is fixedly connected with rudder face 4, from
And realize purpose of the measurement rudder face with respect to deflection angle.
In order to realize that measurement accuracy is 30 ' this index, respectively in 3 high scale number of dial 2 and vernier pointer, dial
Scale value be 1 °, mark number every 5 °, 5.5 ° carved in vernier pointer, to realize that measurement accuracy is 30 ' this index.It surveys
When amount, 0 ° of groove is reading shown in the groove closer to dial groove degree, and 30 ' grooves are close to as half degree.
The cracking rudder face measuring device of the utility model is mounted on aircraft rudder surface, and maintenance personnel is in measurement cracking formula
When the rudder face degree of bias, required numerical value can be conveniently read.The cracking rudder face degree of bias measuring device of the utility model is a kind of
Special machinery is not necessarily to extra power, for measuring the cracking rudder face degree of bias.- 65 °~+65 ° of measurement range.Reading is accurate
To 30 '.
The above, the only optimal specific embodiment of the utility model, but the protection scope of the utility model is not
It is confined to this, anyone skilled in the art within the technical scope disclosed by the utility model, can readily occur in
Change or replacement, should be covered within the scope of the utility model.Therefore, the protection scope of the utility model should be with
Subject to the scope of protection of the claims.
Claims (5)
1. a kind of cracking rudder face degree of bias measuring device based on gravity, which is characterized in that the cracking rudder face degree of bias
Measuring device includes:
Base support, base support include pedestal and the bracket that connect with pedestal integral type；
Dial, dial are arranged to the sector structure with lightening hole, the one end of the center of circle and bracket far from pedestal of dial
Fixed and dial center line is overlapped with the bracket middle line, and is equipped with graduation mark along the arc edge of sector structure；
Vernier pointer, described vernier pointer one end is rotatably set to dial the center point, the vernier pointer other end is arranged to
Measurement portion with certain area, can there is vernier graduation in measurement portion, and vernier graduation and graduation mark cooperate to measure vernier pointer
Deflection angle relative to dial center line.
2. the cracking rudder face degree of bias measuring device according to claim 1 based on gravity, which is characterized in that described
Pedestal quadrangle is equipped with adjustable feet, and adjustable feet is used for adjustment base height.
3. the cracking rudder face degree of bias measuring device according to claim 1 based on gravity, which is characterized in that described
The angle of sector structure is not less than 130 degree, so that every side of dial is not less than 65 from radius to the angle of dial center line
Degree.
4. the cracking rudder face degree of bias measuring device according to claim 1 based on gravity, which is characterized in that described
The scale value of dial is 1 degree, and the vernier graduation value of the measurement portion is 5.5 degree.
5. the cracking rudder face degree of bias measuring device according to claim 4 based on gravity, which is characterized in that described
Graduation mark and vernier graduation are directed to the sector structure center of circle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820183973.7U CN208398849U (en) | 2018-02-02 | 2018-02-02 | A kind of cracking rudder face degree of bias measuring device based on gravity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820183973.7U CN208398849U (en) | 2018-02-02 | 2018-02-02 | A kind of cracking rudder face degree of bias measuring device based on gravity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208398849U true CN208398849U (en) | 2019-01-18 |
Family
ID=65065966
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820183973.7U Active CN208398849U (en) | 2018-02-02 | 2018-02-02 | A kind of cracking rudder face degree of bias measuring device based on gravity |
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| CN (1) | CN208398849U (en) |
Cited By (4)
| 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 |
| CN110626522A (en) * | 2019-09-04 | 2019-12-31 | 大连长丰实业总公司 | Protractor for measuring deflection of airplane aileron |
| CN110823504A (en) * | 2019-12-03 | 2020-02-21 | 中国空气动力研究与发展中心 | Nonmetal wind tunnel test model control surface angle gauge and angle measuring method |
| CN112960140A (en) * | 2021-03-15 | 2021-06-15 | 中国商用飞机有限责任公司 | Horizontal tail trim angle adjusting device |
-
2018
- 2018-02-02 CN CN201820183973.7U patent/CN208398849U/en active Active
Cited By (6)
| 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 |
| CN110626522A (en) * | 2019-09-04 | 2019-12-31 | 大连长丰实业总公司 | Protractor for measuring deflection of airplane aileron |
| CN110823504A (en) * | 2019-12-03 | 2020-02-21 | 中国空气动力研究与发展中心 | Nonmetal wind tunnel test model control surface angle gauge and angle measuring method |
| CN110823504B (en) * | 2019-12-03 | 2021-05-04 | 中国空气动力研究与发展中心 | Nonmetal wind tunnel test model control surface angle gauge and angle measuring method |
| CN112960140A (en) * | 2021-03-15 | 2021-06-15 | 中国商用飞机有限责任公司 | Horizontal tail trim angle adjusting device |
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