CN102944207B - Springback type angle displacement measurement device and measurement method thereof - Google Patents
Springback type angle displacement measurement device and measurement method thereof Download PDFInfo
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- CN102944207B CN102944207B CN201110232671.7A CN201110232671A CN102944207B CN 102944207 B CN102944207 B CN 102944207B CN 201110232671 A CN201110232671 A CN 201110232671A CN 102944207 B CN102944207 B CN 102944207B
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Abstract
The invention discloses a springback type angle displacement measurement device, and belongs to the field of aeronautical engineering test detection. The device is characterized by comprising an angle displacement detecting unit, a springback reset unit, a transmission connecting unit and an installation locating unit, wherein a thrust end of the springback reset unit is fixed at a bearing fixed end of the angle displacement detecting unit; the other thrust end is fixed at a rocker arm of the transmission connecting unit; a tail end of the rocker arm of the transmission connecting unit is fixed on a rotary shaft of the angle displacement detecting unit; an end of the other rocker arm is in contact with an upper surface of the installation locating unit; and the control surface drift angle is measured in a way that the transmission connecting unit follows deflection of the airplane control surface and drives the rotary shaft of the angle displacement detecting unit to deflect. The device has the characteristics of compact and simple structure, small space size, low cost, reliability in operation, high test precision, accordance with the actual motion situation of the airplane control surface, and convenience in installation, usage and adjustment, and is suitable for measurement of drift angles of various airplane control surfaces.
Description
Technical field
The present invention relates to a kind of back springing type angle displacement measuring device, particularly to measurement mechanism and the method thereof of aircraft rudder surface (401) drift angle, belong to aeronautical engineering testing inspection field.
Technical background
At present, in aircraft rudder surface (401) measurement of angle, for specific rudder face (401), it transformed often and complete the measurement of rudder face (401) drift angle; Or design special fixture and connector, use general angular displacement sensor, obliquity sensor or electronic compass to measure rudder face (401) drift angle, illustrate respectively below:
1, specific rudder face (401) is transformed, need to complete measurement of angle unit according to the structure specialized designs of aircraft rudder surface (401), combine as the part of rudder face (401) and rudder face (401).The original function characteristics such as the intensity of rudder face (401) can be affected to the possibility of result that rudder face (401) is transformed, on the other hand, the complex process of transformation aircraft rudder surface (401), implements difficulty large, cause cost also very high, and not there is versatility.
2, special fixture and connector is designed, when using general angular displacement sensor to measure rudder face (401) drift angle, fixture, connector and the angular displacement sensor etc. these disperseed are needed to fit together, vertical and horizontal size is large, need to take very large space, bring very large difficulty to in-site installation and use.
When 3, using obliquity sensor to measure rudder face (401) drift angle, because obliquity sensor dynamic response frequency is low, be difficult to use in the measurement carrying out dynamic characteristic, and obliquity sensor can only be used for the measurement in diving plane rudder face (401) drift angle such as elevator, aileron.
When 4, using electronic compass to measure rudder face (401) drift angle, equally because electronic compass dynamic response frequency is low, also be difficult to use in the measurement carrying out dynamic characteristic, and electronic compass is easily by ferromagnetic ambient influnence, is difficult to adapt to the measurement to aircraft rudder surface (401) drift angle.
Along with the development of microelectric technique, micromachining technology, automatic measurement technology, design one does not need to transform aircraft rudder surface, and easy to install, the condition that can complete aircraft rudder surface declination angle measurement device is ripe.
Summary of the invention
The object of the invention is to design a kind of back springing type angle displacement measuring device, by traditional sensor with measure in fixture, transmission connection piece integrate, and carry force reset unit, can clamping on the aircraft rudder surface of various forms and size; Neither need to transform aircraft rudder surface, also do not need the special fixture of design and connector, meanwhile, reduce the space shared by whole measurement mechanism, aircraft rudder surface can be arranged on easily.
The technical scheme that the present invention takes is: a kind of back springing type angle displacement measuring device comprises Angular Displacement Detecting unit (1), resilience reset unit (2), the unit that is in transmission connection (3), positioning unit (4), the unit (3) that is in transmission connection comprises two rocking arms, be rotationally connected, be respectively the first rocking arm (301) and the second rocking arm (302), resilience reset unit (2) one end is fixedly connected with on Angular Displacement Detecting unit (1), and the other end is fixedly connected with on the first rocking arm (301); First rocking arm (301) is also directly fixedly connected with Angular Displacement Detecting unit (1) rotating shaft; Second rocking arm (302) other end is spacing fixing by installing positioning unit (4).
Further, above-mentioned second rocking arm (302) other end is bulb.
Further, above-mentioned second rocking arm (302) other end is provided with roller.
Further, above-mentioned positioning unit (4) is matrix face.
Further, above-mentioned positioning unit (4) is matrix sphere.
Further, above-mentioned resilience reset unit (2) is extension spring.
The measuring method of above-mentioned a kind of back springing type angle displacement measuring device is used to comprise the following steps:
Step 1: established angle displacement detecting unit (1)
Locus, size, shape etc. according to aircraft rudder surface (401) use fixture established angle displacement detecting unit (1), ensure the rotating shaft of Angular Displacement Detecting unit (1) and the shaft parallel of aircraft rudder surface (401);
Step 2: install positioning unit (4)
According to the size of the first rocking arm (301), aircraft rudder surface (401) is installed positioning unit (4), makes positioning unit (4), the second rocking arm (302) parallel with Angular Displacement Detecting unit (1) plane that rotating shaft is formed with the rotating shaft of aircraft rudder surface (401);
Step 3: adjustment Angular Displacement Detecting unit (1), makes the first rocking arm (301) parallel with aircraft rudder surface (401) surface
Adjustment Angular Displacement Detecting unit (1), make the first rocking arm (301) and aircraft rudder surface (401) surface parallel, ensure by the first rocking arm (301) and second rocking arm (302) of the rotating shaft of Angular Displacement Detecting unit (1) and the rotating shaft line of aircraft rudder surface (401), (3) of the unit that is in transmission connection further, aircraft rudder surface (401) is surperficial forms parallelogram;
Step 4: adjustment resilience reset unit (2), ensures that the second rocking arm (302) fully contacts with fixed installation positioning unit (4) matrix face
Adjustment resilience reset unit (2), one of them force side is fixed on the load stiff end of Angular Displacement Detecting unit (1), another force side is fixed on the first rocking arm (301), ensure that resilience reset unit (2) is applied with predetermined power to the first rocking arm (301), ensure that the second rocking arm (302) other end fully contacts with fixed installation positioning unit (4) matrix face simultaneously;
Step 5: operating aircraft rudder face (401) deflects, makes the first rocking arm (301) follow rudder face (401) motion
Operating aircraft rudder face (401) deflects, when aircraft rudder surface (401) is to a lateral movement away from the unit that is in transmission connection (3), because the first rocking arm (301) is subject to resilience reset unit (2) applied force, first rocking arm (301) deflects and follows the motion of rudder face (401), and aircraft rudder surface (401) is to when a lateral movement of the first rocking arm (301), there will be rudder face (401) to be applied with to the first rocking arm (301) and to be greater than resilience reset unit (2) applied force, first rocking arm (301) deflects equally and follows the motion of rudder face (401),
Step 6: obtain rudder face (401) deflection angle
First rocking arm (301) drives Angular Displacement Detecting unit (1) rotating shaft to rotate, and its deflection angle is consistent with aircraft rudder surface (401) deflection angle, and then obtains the deflection angle of aircraft rudder surface (401).
The present invention has compact conformation, simple, bulk is little, cost is low, reliable operation, measuring accuracy are high, meet aircraft rudder surface (401) deflection actual motion situation, install and use feature easy to adjust, be applicable to the measurement of all kinds aircraft rudder surface (401) drift angle.
Accompanying drawing explanation
Fig. 1 is structure principle chart of the present invention;
Fig. 2 is Angular Displacement Detecting unit of the present invention example structure schematic diagram;
Fig. 3 is resilience reset unit of the present invention example structure schematic diagram;
Fig. 4 is that the present invention is in transmission connection the structure principle chart of a unit embodiment;
Fig. 5 is the principle schematic of one embodiment of the invention;
Wherein: 1: Angular Displacement Detecting unit, 101: rotating shaft, 102: load stiff end, 2: resilience reset unit, 3: be in transmission connection unit, 301: the first rocking arms, 302: the second rocking arms, 303: rotating connector, 304: circular hole, 305: roller, 306: bolt hole, 4: fixed installation positioning unit, 401: rudder face, 402: fixture, 403: rudder face rotating shaft.
Detailed description of the invention
In order to better the present invention is described, below in conjunction with Figure of description and embodiment, the present invention is described in detail.
A kind of back springing type angle displacement measuring device, comprise Angular Displacement Detecting unit 1, resilience reset unit 2, the unit 3 that is in transmission connection, install positioning unit 4, the unit 3 that is in transmission connection is two rocking arms, be respectively the first rocking arm 301 and the second rocking arm 302, connected by rotating connector 303, and at grade, the first rocking arm 301 and the second rocking arm 302 freely rotate around it at grade, and the torsion of the first rocking arm 301 and the second rocking arm 302 and beat are limited in minimum zone; Wherein the end of the first rocking arm 301 is circular hole 304, and rotating shaft 101 consistent size of circular hole 304 size and Angular Displacement Detecting unit 1, has bolt hole 306 in circular hole 304 side, so that the first rocking arm 301 fixing in the rotating shaft 101 of Angular Displacement Detecting unit 1;
Resilience reset unit 2 and the unit 3 that is in transmission connection are fixed in the rotating shaft of Angular Displacement Detecting unit 1 respectively; Angular Displacement Detecting unit 1 has a rotating shaft 101 and load stiff end 102; Resilience reset unit 2 one end is fixed on the load stiff end 102 of Angular Displacement Detecting unit 1, and the other end is fixed on the first rocking arm 301 of the unit 3 that is in transmission connection; In addition, the first rocking arm 301 is also connected with the rotating shaft 101 of Angular Displacement Detecting unit 1 separately, and the other end of the second rocking arm 302 contacts with installation positioning unit 4, spacing fixing to it by installation positioning unit 4.
As an embodiment of resilience reset unit 2, it is extension spring, namely can extend at extended state, and when cancelling tensile force, it can reset, and turns back to original state.
In specific implementation process, in order to ensure that installing positioning unit 4 fixes the spacing of the second rocking arm 302, its end is positioned at all the time installs positioning unit 4 center, and installing positioning unit (4) with the contact surface of the second rocking arm 302 is matrix face.
In specific implementation process, in order to ensure to install relatively fixing to the second rocking arm 302 of the matrix sphere of positioning unit 4, ensure that again the second rocking arm 302 is movable among a small circle, namely spacing, above-mentioned second rocking arm 302 other end is bulb, can reduce itself and the resistance of matrix sphere installing positioning unit 4 like this.
As a kind of variant of bulb, it can be roller 305, also can be other forms.
As a kind of variant in matrix face, above-mentioned matrix face is matrix sphere.
The measuring method of above-mentioned a kind of back springing type angle displacement measuring device is used to comprise the following steps:
Step 1: established angle displacement detecting unit 1
Use fixture 402 established angle displacement detecting unit 1 according to the locus of aircraft rudder surface 401, size, shape, ensure that the rotating shaft 101 of Angular Displacement Detecting unit 1 is parallel with the rudder face rotating shaft 403 of aircraft rudder surface 401;
Step 2: install positioning unit 4
According to the size of the first rocking arm 301, aircraft rudder surface 401 is installed positioning unit 4, make the rudder face rotating shaft 403 of positioning unit 4, second rocking arm 302 and aircraft rudder surface 401 and Angular Displacement Detecting unit 1 rotating shaft 101 to form plane parallel;
Step 3: adjustment Angular Displacement Detecting unit 1, makes the first rocking arm 301 parallel with aircraft rudder surface 401 surface
Adjustment Angular Displacement Detecting unit 1, make the first rocking arm 301 parallel with aircraft rudder surface 401 surface, ensure further to form parallelogram by the rotating shaft 101 of Angular Displacement Detecting unit 1 and the first rocking arm 301 of rudder face rotating shaft 403 line of aircraft rudder surface 401,3 of the unit that is in transmission connection and the second rocking arm 302, aircraft rudder surface 401 surface;
Step 4: adjustment resilience reset unit 2, ensures that the second rocking arm 302 fully contacts with fixed installation positioning unit 4 matrix face
Adjustment resilience reset unit 2, one of them force side is fixed on the load stiff end 102 of Angular Displacement Detecting unit 1, another force side is fixed on the first rocking arm 301, ensure that resilience reset unit 2 is applied with predetermined power to the first rocking arm 301, ensure that second rocking arm 302 other end fully contacts with fixed installation positioning unit 4 matrix face simultaneously;
Step 4: operating aircraft rudder face 401 deflects, makes the first rocking arm 301 follow rudder face 401 and moves
Operating aircraft rudder face 401 deflects, when aircraft rudder surface 401 is to a lateral movement away from the unit 3 that is in transmission connection, because the first rocking arm 301 is subject to resilience reset unit 2 applied force, first rocking arm 301 deflects and follows the motion of rudder face 401, and aircraft rudder surface 401 is to when a lateral movement of the first rocking arm 301, there will be rudder face 401 to be applied with to the first rocking arm 301 and to be greater than resilience reset unit 2 applied force, the first rocking arm 301 deflects equally and follows the motion of rudder face 401;
Step 6: obtain rudder face 401 deflection angle
First rocking arm 301 drives Angular Displacement Detecting unit 1 rotating shaft 101 to rotate, and its deflection angle is consistent with aircraft rudder surface 401 deflection angle, and then obtains the deflection angle of aircraft rudder surface 401.
Claims (1)
1. a measuring method for back springing type angle displacement measuring device, comprises the following steps:
Step 1: established angle displacement detecting unit (1)
Use fixture established angle displacement detecting unit according to the locus of aircraft rudder surface (401), size, shape, ensure the rotating shaft of Angular Displacement Detecting unit (1) and the shaft parallel of aircraft rudder surface (401);
Step 2: install positioning unit (4)
According to the size of the first rocking arm (301), aircraft rudder surface (401) is installed positioning unit (4), ensures that positioning unit (4), the second rocking arm (302) are parallel with Angular Displacement Detecting unit (1) plane that rotating shaft is formed with the rotating shaft of aircraft rudder surface (401);
Step 3: adjustment Angular Displacement Detecting unit, ensures that the first rocking arm (301) is parallel with aircraft rudder surface (401) surface
Adjustment Angular Displacement Detecting unit (1), ensure that the first rocking arm (301) and aircraft rudder surface (401) surface is parallel, ensure by rotating shaft line, the first rocking arm (301) and second rocking arm (302) of the rotating shaft of Angular Displacement Detecting unit and aircraft rudder surface (401) further, aircraft rudder surface (401) is surperficial forms parallelogram;
Step 4: adjustment resilience reset unit (2), ensures that the second rocking arm (302) fully contacts with fixed installation positioning unit (4) matrix face
Adjustment resilience reset unit (2), one of them force side is fixed on the load stiff end of Angular Displacement Detecting unit (1), another force side is fixed on the first rocking arm (301), ensure that resilience reset unit (2) is applied with predetermined power to the first rocking arm (301), ensure that the second rocking arm (302) fully contacts with fixed installation positioning unit matrix face simultaneously;
Step 5: operating aircraft rudder face (401) deflects, makes the first rocking arm (301) follow rudder face (401) motion;
Step 6: obtain rudder face (401) deflection angle
First rocking arm (301) drives Angular Displacement Detecting unit (1) rotating shaft to rotate, and its deflection angle is consistent with aircraft rudder surface (401) deflection angle, and then obtains the deflection angle of aircraft rudder surface (401).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110232671.7A CN102944207B (en) | 2011-08-15 | 2011-08-15 | Springback type angle displacement measurement device and measurement method thereof |
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| CN201110232671.7A CN102944207B (en) | 2011-08-15 | 2011-08-15 | Springback type angle displacement measurement device and measurement method thereof |
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| CN102944207B true CN102944207B (en) | 2015-04-29 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107764226B (en) * | 2017-11-09 | 2020-02-18 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Four corners displacement sensor overall arrangement transmission structure |
| CN111102951A (en) * | 2019-12-25 | 2020-05-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Take spring sensor output rocking arm |
| CN112461184B (en) * | 2020-11-10 | 2022-05-27 | 中航通飞华南飞机工业有限公司 | Water rudder deflection angle measuring device |
| CN113137947A (en) * | 2021-03-18 | 2021-07-20 | 华能煤炭技术研究有限公司 | Angle measuring device, attitude measurement and control system and fully mechanized mining equipment |
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