CN112896549B - General fixed wing aircraft rudder angle detection device - Google Patents
General fixed wing aircraft rudder angle detection device Download PDFInfo
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- CN112896549B CN112896549B CN202110082133.8A CN202110082133A CN112896549B CN 112896549 B CN112896549 B CN 112896549B CN 202110082133 A CN202110082133 A CN 202110082133A CN 112896549 B CN112896549 B CN 112896549B
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- sliding rod
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention belongs to the technical field of aircraft maintenance measuring tools, and particularly discloses a universal fixed wing aircraft control surface deflection angle detection device which comprises an elastic clamping device, wherein the elastic clamping device comprises an upper clamping plate and a lower clamping plate, an upper clamping plate is arranged at the lower part of the upper clamping plate, a lower clamping plate is arranged at the upper part of the lower clamping plate, the upper clamping plate and the lower clamping plate are arranged in an axial symmetry manner, a horizontal sliding rod is vertically and slidably connected onto the upper clamping plate, a fixing part for fixing the sliding rod is arranged at the upper part of the sliding rod, a horizontal round rod is arranged at one side, far away from the upper clamping plate, of the lower part of the sliding rod, a flat plate is rotatably connected onto one side, far away from the sliding rod, of the round rod in an axial direction, a protractor is coaxially and rotatably connected onto one side, close to the sliding rod, and comprises an arc-shaped angle plate, the axis of the angle plate is coincident with the axis of the round rod, and a level is arranged on the angle plate. The scheme is mainly applied to measuring the deflection angle of the elevator or the aileron of the airplane, and solves the problems that an angle measuring instrument used in the prior art is complex to operate and takes long time in the using process.
Description
Technical Field
The invention belongs to the technical field of airplane maintenance measuring tools, and particularly discloses a general detection device for a deflection angle of a control surface of a fixed-wing airplane.
Background
In certain aircraft, soft operating systems are used, which are made of stainless steel wires, which have the advantage of being resistant to corrosion, but have the disadvantage of being less resistant to wear. In recent years, as the flight time increases, the wire breakage of the operating wire rope occurs many times, and even the entire wire rope breaks, and in order to prevent the occurrence of the failure, the inspection frequency of the operating wire rope must be increased. After the wire-broken steel cable is replaced or the tension is adjusted in season, the deflection angle of the control surface must be checked and adjusted, and the deflection angle is guaranteed to be within the range required by a maintenance manual. In the past, the measurement is carried out by using an electronic angle meter for a long time, each measurement is very inconvenient, a large number of working hours are needed, and the operation is complicated and is not intuitive.
Disclosure of Invention
The invention aims to provide a device for detecting the deflection angle of a control surface of a general fixed wing aircraft, which aims to solve the problems of complex operation and long time consumption of an angle measuring instrument used in the prior art in the process of measuring the deflection angle of an elevator or an aileron.
In order to achieve the purpose, the technical scheme of the invention is as follows: general fixed wing aircraft rudder angle of deflection detection device, including elasticity clamping device, elasticity clamping device includes the punch holder, the lower plate, the punch holder lower part is equipped with the cardboard, lower plate upper portion is equipped with down the cardboard, go up cardboard and cardboard axial symmetry arrangement down, vertical sliding connection has the horizontally slide bar on the last cardboard, slide bar upper portion is equipped with the fixed part that is used for fixed slide bar, one side that the cardboard was kept away from to the slide bar lower part is equipped with the horizontally round bar, one side of keeping away from the slide bar on the round bar is connected with the flat board around axial rotation, one side coaxial rotation that is close to the slide bar on the round bar is connected with the protractor, the protractor includes the angle board of arcuation, the axis of angle board and the coincidence of round bar, be equipped with the spirit level on the angle board.
The working principle of the technical scheme is as follows:
when the measuring tool is used, the upper clamping plate and the lower clamping plate are clamped on the ailerons or the elevator, the edges of the ailerons or the elevator are arranged between the upper clamping plate and the lower clamping plate, and the ailerons or the elevator clamped in by the upper clamping plate and the lower clamping plate can be positioned on an angular bisector formed by the upper clamping plate and the lower clamping plate; when deflecting the angular surveying, vertical can drive the flat board to the slip slide bar and reciprocate, and the fixed part can be fixed the position of slide bar, rotates the flat board and can paste the flat board on the string of a thread in aileron or elevator, then the turned angle board makes zero scale mark on the angle board be in horizontal position through the spirit level, then reads the contained angle that zero scale mark constitutes on flat board and the angle board, then has: angle-the angle of inclination of a wing or horizontal tail (known) is the angle of deflection of an aileron or elevator.
The beneficial effects of this technical scheme lie in:
(1) according to the scheme, the upper clamping plate is arranged at the lower part of the upper clamping plate, and the lower clamping plate is arranged at the upper part of the lower clamping plate, so that the ailerons or the elevator clamped between the upper clamping plate and the lower clamping plate can be conveniently positioned and arranged on the angle bisection line formed by the upper clamping plate and the lower clamping plate, and the angle measurement precision is improved;
(2) this scheme is through rotating connection flat board and protractor on the round bar, sets up the spirit level simultaneously on the protractor, makes whole easy operation, convenience, has improved work efficiency.
Furthermore, the level gauge is a liquid level gauge, a through hole is formed in the middle of the angle plate, and the liquid level gauge is horizontally arranged in the through hole. The structure is simple, and the manufacture is convenient.
Furthermore, an indicating plate is arranged on one side of the flat plate, which is close to the angle plate, and the indicating plate is arranged on the central line of the flat plate in the height direction. The thickness of the indicator plate is smaller than that of the flat plate, so that the accuracy of angle reading can be further improved.
Further, the vertical sliding connection mode of the sliding rod and the upper clamping plate is as follows: go up and follow on the cardboard vertical to having seted up T shape spout, the slide bar on be close to the slider of last cardboard for with T shape spout adaptation. The structure is simple, and the stability is high.
Furthermore, the fixed part is including setting up the riser on slide bar upper portion, and the one side of keeping away from last cardboard on the riser has the hand to screwed bolt along the level to threaded connection. The bolt is screwed by hand to facilitate operation.
Furthermore, one side of the upper clamping plate, which is far away from the clamping opening, is provided with an upper handle, and one side of the lower clamping plate, which is far away from the clamping opening, is provided with a lower handle. The upper clamping plate and the lower clamping plate can be clamped conveniently through the upper handle and the lower handle.
Furthermore, the upper clamping plate and the lower clamping plate are provided with cushion layers on the opposite sides of the clamping opening. The soft cushion layer can prevent the ailerons or the elevators from being scratched by the upper clamping plate and the lower clamping plate.
Drawings
FIG. 1 is a schematic diagram of a northwest isometric structure of an embodiment of a general fixed-wing aircraft control surface deflection angle detection device according to the invention;
FIG. 2 is an enlarged view taken at A in FIG. 1;
FIG. 3 is a left side view of FIG. 1;
FIG. 4 is a schematic representation of a southwest isometric construction for flap deflection angle measurement;
FIG. 5 is a left side view of FIG. 4;
FIG. 6 is an enlarged view at B in FIG. 5;
fig. 7 is an explanatory view of the flap deflection angle calculation.
Detailed Description
The following is further detailed by way of specific embodiments:
reference numerals in the drawings of the specification include: the device comprises an upper clamping plate 1, a lower clamping plate 2, an upper clamping plate 3, a lower clamping plate 4, a sliding rod 5, a round rod 6, a flat plate 7, an angle plate 8, a liquid level meter 9, an indicating plate 10, a vertical plate 11, a hand-screwed bolt 12, a wing 13, an aileron 14, an aileron chord line 15, a wing chord line 16 and a horizontal line 17.
The embodiment is shown in fig. 1, the universal fixed wing aircraft control surface deflection angle detection device comprises an elastic clamping device, the elastic clamping device comprises an upper clamping plate 1 and a lower clamping plate 2, an upper clamping plate 3 is welded on the lower portion of the upper clamping plate 1, a lower clamping plate 4 is welded on the upper portion of the lower clamping plate 2, the upper clamping plate 3 and the lower clamping plate 4 are arranged in an axial symmetry mode, a horizontal sliding rod 5 is vertically and slidably connected to the upper clamping plate 3, and a fixing portion used for fixing the sliding rod 5 is arranged on the upper portion of the sliding rod 5.
As shown in fig. 2 and fig. 3, in the present embodiment, the vertical sliding connection between the sliding rod 5 and the upper card board 3 is as follows: a T-shaped sliding groove is formed in the upper edge of the upper clamping plate 3 in the vertical direction, and a sliding block matched with the T-shaped sliding groove is arranged at one end, close to the upper clamping plate 3, of the sliding rod 5.
As shown in fig. 2 and 3, the fixing portion in this embodiment includes a vertical plate 11 welded to the upper portion of the sliding rod 5, and a hand bolt 12 is screwed to one side of the vertical plate 11 away from the upper clamping plate 3 along the horizontal direction.
As shown in fig. 2 and 3, a horizontal round rod 6 is welded on one side of the lower portion of the sliding rod 5, which is far away from the upper clamping plate 3, a flat plate 7 is rotatably connected on one side of the round rod 6, which is far away from the sliding rod 5, in an axial direction, a protractor is rotatably connected on one side of the round rod 6, which is close to the sliding rod 5, in a coaxial manner, and comprises an arc-shaped angle plate 8, the axis of the angle plate 8 coincides with the axis of the round rod 6, a through hole is processed in the middle of the angle plate 8, and a liquid level gauge 9 is horizontally installed in the through hole.
An indicating plate 10 is arranged on one side of the flat plate 7 close to the angle plate 8, the thickness of the indicating plate 10 is smaller than that of the flat plate 7, and the indicating plate 10 is arranged on a central line of the flat plate 7 in the height direction.
An upper handle is arranged on one side of the upper clamping plate 1, which is far away from the clamping opening, and a lower handle is arranged on one side of the lower clamping plate 2, which is far away from the clamping opening.
The opposite sides of the clamping opening of the upper splint 1 and the lower splint 2 are both stuck with soft cushion layers, and the soft cushion layers in the embodiment are preferably EVA or PU.
The specific implementation process is as follows:
as shown in fig. 4, 5 and 6, the following describes the use of the measuring tool by measuring the deflection angle of the flap 14, when the measuring tool is in use, the upper clamping plate 1 and the lower clamping plate 2 are clamped on the flap 14, the edge of the flap 14 is arranged between the upper clamping plate 3 and the lower clamping plate 4, and the upper clamping plate 3 and the lower clamping plate 4 can enable the clamped flap 14 to be positioned on the bisector of the angle formed by the upper clamping plate 3 and the lower clamping plate 4; during deflection angle measurement, a force is applied to slide the slide rod 5 downwards, the slide rod 5 moves downwards to drive the flat plate 7 to move downwards, then the flat plate 7 is rotated to enable the flat plate 7 to be attached to a chord line of the aileron 14, the slide rod 5 is fixed by screwing a hand bolt 12 on the vertical plate 11, then the angle plate 8 is rotated, a zero scale line on the angle plate 8 is in a horizontal position through the liquid level meter 9, then an included angle formed by the indicating plate 10 and the zero scale line on the angle plate 8 is read, as shown in fig. 7, angle B is an angle formed by an aileron line 15 and a horizontal line 17, angle D is an angle formed by a wing chord line 16 and the horizontal line 17, and angle E is a deflection angle of the aileron 14 relative to the wing 13, and the method comprises the following steps: the angle a is equal to angle B, the angle C is equal to angle D, and therefore: the deflection angle of the aileron 14 can be calculated by directly measuring ═ a ═ B ═ D ═ a ═ C, wherein ═ C is known.
The foregoing is merely an example of the present invention and common general knowledge of known specific structures and features of the embodiments is not described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent.
Claims (7)
1. General fixed wing aircraft rudder angle of deflection detection device, including elasticity clamping device, a serial communication port, elasticity clamping device includes the punch holder, the lower plate, the punch holder lower part is equipped with the cardboard, lower plate upper portion is equipped with down the cardboard, go up cardboard and lower cardboard axisymmetric arrangement, vertical sliding connection has the horizontally slide bar on the last cardboard, slide bar upper portion is equipped with the fixed part that is used for fixed slide bar, the slide bar lower part is kept away from one side of last cardboard and is equipped with the horizontally pole, one side of keeping away from the slide bar on the pole is connected with the flat board around the axial rotation, one side coaxial rotation that is close to the slide bar on the pole is connected with the protractor, the protractor includes the angle board of arcuation, the axis of angle board and the coincidence of pole, be equipped with the spirit level on the angle board.
2. The device for detecting the control surface deflection angle of a general fixed-wing aircraft according to claim 1, wherein the level gauge is a liquid level gauge, a through hole is formed in the middle of the angle plate, and the liquid level gauge is horizontally arranged in the through hole.
3. The rudder angle detecting device for a general fixed wing aircraft according to claim 2, wherein an indicating plate is provided on a side of the flat plate adjacent to the angle plate, the indicating plate being disposed on a center line in a height direction of the flat plate.
4. The device for detecting the control surface deflection angle of the general fixed-wing aircraft according to claim 3, wherein the vertical sliding connection mode of the sliding rod and the upper clamping plate is as follows: go up and follow on the cardboard vertical to having seted up T shape spout, the slide bar on be close to the slider of last cardboard for with T shape spout adaptation.
5. The device for detecting the rudder surface deflection angle of a general fixed wing aircraft as claimed in claim 4, wherein the fixing portion comprises a vertical plate disposed at an upper portion of the sliding rod, and a hand bolt is screwed on a side of the vertical plate away from the upper clamping plate along a horizontal direction.
6. The apparatus of claim 5, wherein the upper clamp plate has an upper handle on a side away from the clamping opening, and the lower clamp plate has a lower handle on a side away from the clamping opening.
7. The device for detecting the rudder surface deflection angle of a general fixed-wing aircraft according to claim 6, wherein the upper clamping plate and the lower clamping plate are provided with cushion layers on opposite sides of the clamping opening.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110082133.8A CN112896549B (en) | 2021-01-21 | 2021-01-21 | General fixed wing aircraft rudder angle detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110082133.8A CN112896549B (en) | 2021-01-21 | 2021-01-21 | General fixed wing aircraft rudder angle detection device |
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| Publication Number | Publication Date |
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| CN112896549A CN112896549A (en) | 2021-06-04 |
| CN112896549B true CN112896549B (en) | 2022-07-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110082133.8A Active CN112896549B (en) | 2021-01-21 | 2021-01-21 | General fixed wing aircraft rudder angle detection device |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113968358A (en) * | 2021-10-28 | 2022-01-25 | 西安羚控电子科技有限公司 | Operation inspection method and system of fixed-wing unmanned aerial vehicle |
| CN117232438B (en) * | 2023-11-13 | 2024-03-15 | 成都飞机工业（集团）有限责任公司 | Device for measuring deflection angle of movable airfoil surface of airplane, calibration device and calibration method |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3996670A (en) * | 1974-08-19 | 1976-12-14 | United Technologies Corporation | Protractor with digital readout |
| JP2006119082A (en) * | 2004-10-25 | 2006-05-11 | Hitachi Cable Ltd | Steering angle detecting device |
| JP2008101936A (en) * | 2006-10-17 | 2008-05-01 | Toto Ltd | Angle measurement tool, and inspecting system of trim tile using angle measurement tool |
| JP4912212B2 (en) * | 2007-05-09 | 2012-04-11 | ジャパン・ハムワージ株式会社 | Steering angle detection device for steering machine |
| CN204064205U (en) * | 2014-08-22 | 2014-12-31 | 安徽安凯汽车股份有限公司 | A kind of passenger vehicle each pilot hole angular deviation pick-up unit |
| DE102015101328A1 (en) * | 2015-01-29 | 2016-08-04 | Airbus Operations Gmbh | System and method for repairing a component made from a plastic |
| CN105526904B (en) * | 2015-11-30 | 2017-12-19 | 中航飞机股份有限公司西安飞机分公司 | A kind of aircraft rudder surface declination angle measurement device |
| CN105423910B (en) * | 2015-12-28 | 2019-03-15 | 中国航天空气动力技术研究院 | Deflection angle of airplane control surface degree measuring device and method |
| CN108091179A (en) * | 2017-12-15 | 2018-05-29 | 中国民用航空飞行学院 | Aircraft flight real-time status monitoring system based on ATG technologies |
| 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 |
| CN208313197U (en) * | 2018-06-15 | 2019-01-01 | 东汉太阳能无人机技术有限公司 | Aircraft rudder surface deflection angle measurement device |
| CN109458971A (en) * | 2018-12-16 | 2019-03-12 | 山西汾西重工有限责任公司 | Underwater detectoscope rudder angle debugs measuring mechanism and measurement method |
| CN110626522A (en) * | 2019-09-04 | 2019-12-31 | 大连长丰实业总公司 | Protractor for measuring deflection of airplane aileron |
| CN110589024A (en) * | 2019-09-30 | 2019-12-20 | 西安爱生技术集团公司 | Control surface measuring device of fixed wing unmanned aerial vehicle |
| CN111412822A (en) * | 2020-04-09 | 2020-07-14 | 贵州航天风华精密设备有限公司 | Control surface deflection angle measuring tool and measuring method thereof |
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