CN102944207A - Springback type angle displacement measurement device and measurement method thereof - Google Patents
Springback type angle displacement measurement device and measurement method thereof Download PDFInfo
- Publication number
- CN102944207A CN102944207A CN2011102326717A CN201110232671A CN102944207A CN 102944207 A CN102944207 A CN 102944207A CN 2011102326717 A CN2011102326717 A CN 2011102326717A CN 201110232671 A CN201110232671 A CN 201110232671A CN 102944207 A CN102944207 A CN 102944207A
- Authority
- CN
- China
- Prior art keywords
- unit
- rocking arm
- displacement detecting
- detecting unit
- angular displacement
- 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.)
- Granted
Links
Images
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 test detection field.
Technical background
At present, in aircraft rudder surface (401) measurement of angle, for specific rudder face (401) it is transformed often and finish the measurement of rudder face (401) drift angle; Or design special anchor clamps and web member, and use general angular displacement sensor, obliquity sensor or electronic compass to measure rudder face (401) drift angle, the below illustrates respectively:
1, specific rudder face (401) is transformed, need to be finished the measurement of angle unit according to the structure specialized designs of aircraft rudder surface (401), combine as a part and the rudder face (401) of rudder face (401).Can affect the original function characteristics such as intensity of rudder face (401) on the possibility of result of rudder face (401) transformation, on the other hand, transform the complex process of aircraft rudder surface (401), implement difficulty large, cause cost also very high, and do not have versatility.
2, special anchor clamps and the web member of design, when using general angular displacement sensor to measure rudder face (401) drift angle, anchor clamps, web member and the angular displacement sensor etc. of these dispersions need to be fitted together, the vertical and horizontal size is large, need to take very large space, bring very large difficulty for on-the-spot installation and use.
When 3, using obliquity sensor to measure rudder face (401) drift angle, because the obliquity sensor dynamic response frequency is low, be difficult to use in the measurement of carrying out dynamic perfromance, and obliquity sensor can only be used for to the measurement in diving plane rudder face (401) drift angle such as elevating rudder, aileron.
When 4, using electronic compass to measure rudder face (401) drift angle, it is same because the electronic compass dynamic response frequency is low, also be difficult to use in the measurement of carrying out dynamic perfromance, and electronic compass easily is subjected to ferromagnetic environmental impact, the very difficult measurement that adapts to aircraft rudder surface (401) drift angle.
Along with the development of microelectric technique, micromachining technology, automatic measurement technology, design a kind of the needs aircraft rudder surface is transformed, easy to install, the condition that can finish the aircraft rudder surface declination angle measurement device is ripe.
Summary of the invention
The objective of the invention is to design a kind of back springing type angle displacement measuring device, anchor clamps, transmission connection piece in traditional sensor and the measurement are integrated, and carry application of force reset unit, the energy clamping is on the aircraft rudder surface of various forms and size; Neither need aircraft rudder surface is transformed, also do not need to design special anchor clamps and web member, simultaneously, dwindle the shared space of whole measurement mechanism, can be installed in easily aircraft rudder surface.
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 ends are fixedly connected with on the Angular Displacement Detecting unit (1), and the other end is fixedly connected with on the first rocking arm (301); The first rocking arm (301) also directly is fixedly connected with Angular Displacement Detecting unit (1) rotating shaft; The second rocking arm (302) other end is spacing fixing by positioning unit (4) is installed.
Further, above-mentioned the second rocking arm (302) other end is bulb.
Further, above-mentioned the second rocking arm (302) other end is equipped with roller.
Further, above-mentioned positioning unit (4) is the matrix face.
Further, above-mentioned positioning unit (4) is the matrix sphere.
Further, above-mentioned resilience reset unit (2) is extension spring.
Use the measuring method of above-mentioned a kind of back springing type angle displacement measuring device may further comprise the steps:
Step 1: established angle displacement detecting unit (1)
Use special anchor clamps established angle displacement detecting unit (1) according to the locus of aircraft rudder surface (401), size, shape etc., guarantee the rotating shaft of Angular Displacement Detecting unit (1) and the shaft parallel of aircraft rudder surface (401);
Step 2: positioning unit (4) is installed
Size according to the first rocking arm (301), at aircraft rudder surface (401) positioning unit (4) is installed, is made rotating shaft and Angular Displacement Detecting unit (1) plane parallel that rotating shaft forms of positioning unit (4), the second rocking arm (302) and aircraft rudder surface (401);
Step 3: adjust Angular Displacement Detecting unit (1), make the first rocking arm (301) parallel with aircraft rudder surface (401) surface
Adjust Angular Displacement Detecting unit (1), make the first rocking arm (301) and aircraft rudder surface (401) surface parallel, further guarantee by first rocking arm (301) of the rotating shaft of Angular Displacement Detecting unit (1) and (3) of the rotating shaft line of aircraft rudder surface (401), the unit that is in transmission connection and the second rocking arm (302), the surperficial parallelogram that forms of aircraft rudder surface (401);
Step 4: adjust resilience reset unit (2), guarantee that the second rocking arm (302) fully contacts with fixed installation positioning unit (4) matrix face
Adjust 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), guarantee that resilience reset unit (2) is applied with predetermined power to the first rocking arm (301), guarantee that simultaneously the second rocking arm (302) other end fully contacts with fixed installation positioning unit (4) matrix face;
Step 4: operating aircraft rudder face (401) deflection makes the first rocking arm (301) follow rudder face (401) motion
Operating aircraft rudder face (401) deflection, when aircraft rudder surface (401) to away from the lateral movement of the unit that is in transmission connection (3) time, because the first rocking arm (301) is subject to resilience reset unit (2) applied force, (301) deflection of the first rocking arm is also followed the motion of rudder face (401), and aircraft rudder surface (401) is near a lateral movement of the first rocking arm (301) time, rudder face (401) can occur and apply greater than resilience reset unit (2) applied force to the first rocking arm (301), the same deflection of the first rocking arm (301) is also followed the motion of rudder face (401);
Step 6: obtain rudder face (401) deflection angle
The first rocking arm (301) drives Angular Displacement Detecting unit (1) rotating shaft rotation, 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 characteristics easy to adjust, be applicable to the measurement of all kinds aircraft rudder surface (401) drift angle.
Description of drawings
Fig. 1 is structure principle chart of the present invention;
Fig. 2 is the example structure schematic diagram in Angular Displacement Detecting of the present invention unit;
Fig. 3 is example structure schematic diagram of resilience reset unit of the present invention;
Fig. 4 is the be in transmission connection structure principle chart of the embodiment in unit of the present invention;
Fig. 5 is the principle schematic of one embodiment of the invention;
Wherein: 1: Angular Displacement Detecting unit, 101: rotating shaft, 102: the load stiff end, 2: resilience reset unit, 3: the unit that is in transmission connection, 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: anchor clamps, 403: the rudder face rotating shaft.
Embodiment
For better explanation the present invention, 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, positioning unit 4 be installed, 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, connect 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 reversing with beat of the first rocking arm 301 and the second rocking arm 302 is 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 sizes and Angular Displacement Detecting unit 1 have bolt hole 306 in circular hole 304 sides, so that the first rocking arm 301 fixing in the rotating shaft 101 of Angular Displacement Detecting unit 1;
As an embodiment of resilience reset unit 2, it is extension spring, namely can extend at extended state, and when the cancellation tensile force, it can reset, and turns back to original state.
In specific implementation process, in order to guarantee that the spacing fixing of 4 pairs of the second rocking arms 302 of positioning unit is installed, its end is positioned at positioning unit 4 centers of installing all the time, and the surface of contact that positioning unit (4) and the second rocking arm 302 are installed is the matrix face.
In specific implementation process, for relatively fixing to the second rocking arm 302 of the matrix sphere that guarantees to install positioning unit 4, guarantee that again the second rocking arm 302 is movable among a small circle, namely spacing, above-mentioned the second rocking arm 302 other ends are bulb, can reduce like this itself and the resistance of the matrix sphere that positioning unit 4 is installed.
As a kind of form of distortion of bulb, it can be roller 305, also can be other forms.
As a kind of form of distortion of matrix face, above-mentioned matrix face is the matrix sphere.
Use the measuring method of above-mentioned a kind of back springing type angle displacement measuring device may further comprise the steps:
Step 1: established angle displacement detecting unit 1
Use special-purpose anchor clamps 402 established angle displacement detecting unit 1 according to the locus of aircraft rudder surface 401, size, shape etc., guarantee 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: positioning unit 4 is installed
According to the size of the first rocking arm 301, at aircraft rudder surface 401 positioning unit 4 is installed, make rudder face rotating shaft 403 and Angular Displacement Detecting unit 1 rotating shaft 101 plane parallel that forms of positioning unit 4, the second rocking arm 302 and aircraft rudder surface 401;
Step 3: adjust Angular Displacement Detecting unit 1, make the first rocking arm 301 parallel with aircraft rudder surface 401 surfaces
Adjust Angular Displacement Detecting unit 1, make the first rocking arm 301 and aircraft rudder surface 401 surfaces parallel, further guarantee to form parallelogram by 3 the first rocking arm 301 and the second rocking arm 302, aircraft rudder surface 401 surfaces of the rotating shaft 101 of Angular Displacement Detecting unit 1 and rudder face rotating shaft 403 lines of aircraft rudder surface 401, the unit that is in transmission connection;
Step 4: adjust resilience reset unit 2, guarantee that the second rocking arm 302 fully contacts with fixed installation positioning unit 4 matrix faces
Adjust 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, guarantee that resilience reset unit 2 is applied with predetermined power to the first rocking arm 301, guarantee simultaneously the second rocking arm 302 other ends and fixedly mount positioning unit 4 matrix faces and fully contact;
Step 4: 401 deflections of operating aircraft rudder face make the first rocking arm 301 follow rudder face 401 motions
401 deflections of operating aircraft rudder face, when aircraft rudder surface 401 to away from a lateral movement of the unit 3 that is in transmission connection the time, because the first rocking arm 301 is subject to resilience reset unit 2 applied forces, 301 deflections of the first rocking arm are also followed the motion of rudder face 401, and aircraft rudder surface 401 is near a lateral movement of the first rocking arm 301 time, rudder face 401 can occur and apply greater than resilience reset unit 2 applied forces to the first rocking arm 301, the 301 same deflections of the first rocking arm are also followed the motion of rudder face 401;
Step 6: obtain rudder face 401 deflection angles
The first rocking arm 301 drives 1 rotating shaft, 101 rotations of Angular Displacement Detecting unit, and its deflection angle is consistent with aircraft rudder surface 401 deflection angles, and then obtains the deflection angle of aircraft rudder surface 401.
Claims (7)
1. a 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 ends are fixedly connected with on the Angular Displacement Detecting unit (1), and the other end is fixedly connected with on the first rocking arm (301); The first rocking arm (301) also directly is fixedly connected with Angular Displacement Detecting unit (1) rotating shaft; The second rocking arm (302) other end is spacing fixing by positioning unit (4) is installed.
2. back springing type angle displacement measuring device according to claim 1, it is characterized in that: resilience reset unit (2) is extension spring.
3. back springing type angle displacement measuring device according to claim 1, it is characterized in that: the second rocking arm (302) other end is bulb.
4. back springing type angle displacement measuring device according to claim 1, it is characterized in that: the second rocking arm (302) other end is equipped with roller.
5. back springing type angle displacement measuring device according to claim 1, it is characterized in that: positioning unit (4) is the matrix face.
6. back springing type angle displacement measuring device according to claim 4, it is characterized in that: positioning unit (4) is the matrix sphere.
7. the measuring method of a back springing type angle displacement measuring device may further comprise the steps:
Step 1: established angle displacement detecting unit (1)
Use special anchor clamps established angle displacement detecting unit according to the locus of aircraft rudder surface (401), size, shape etc., guarantee the rotating shaft of Angular Displacement Detecting unit (1) and the shaft parallel of aircraft rudder surface (401);
Step 2: positioning unit (4) is installed
Size according to the first rocking arm (301), at aircraft rudder surface (401) single (4) unit in location is installed, guarantees rotating shaft and Angular Displacement Detecting unit (1) plane parallel that rotating shaft forms of positioning unit (4), the second rocking arm (302) and aircraft rudder surface (401);
Step 3: adjust the Angular Displacement Detecting unit, guarantee that the first rocking arm (301) is parallel with aircraft rudder surface (401) surface
Adjust Angular Displacement Detecting unit (1), guarantee that the first rocking arm (301) is parallel with aircraft rudder surface (401) surface, further guarantee to form parallelogram by the rotating shaft of Angular Displacement Detecting unit and rotating shaft line, the first rocking arm (301) and the second rocking arm (302), aircraft rudder surface (401) surface of aircraft rudder surface (401);
Step 4: adjust resilience reset unit (2), guarantee that the second rocking arm (302) fully contacts with fixed installation positioning unit (4) matrix face
Adjust 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), guarantee that resilience reset unit (2) is applied with predetermined power to the first rocking arm (301), guarantee that simultaneously the second rocking arm (302) fully contacts with fixed installation positioning unit matrix face;
Step 4: operating aircraft rudder face (401) deflection makes the first rocking arm (301) follow rudder face (401) motion
Step 6: obtain rudder face (401) deflection angle
The first rocking arm (301) drives Angular Displacement Detecting unit (1) rotating shaft rotation, and its deflection angle is consistent with aircraft rudder surface (401) deflection angle, and then obtains the deflection angle of aircraft rudder surface (401).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110232671.7A CN102944207B (en) | 2011-08-15 | 2011-08-15 | Springback type angle displacement measurement device and measurement method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110232671.7A CN102944207B (en) | 2011-08-15 | 2011-08-15 | Springback type angle displacement measurement device and measurement method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102944207A true CN102944207A (en) | 2013-02-27 |
| CN102944207B CN102944207B (en) | 2015-04-29 |
Family
ID=47727172
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110232671.7A Active CN102944207B (en) | 2011-08-15 | 2011-08-15 | Springback type angle displacement measurement device and measurement method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102944207B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107764226A (en) * | 2017-11-09 | 2018-03-06 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of four angular displacement sensors layout drive mechanism |
| 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 |
| CN112461184A (en) * | 2020-11-10 | 2021-03-09 | 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2035870U (en) * | 1988-09-29 | 1989-04-12 | 航天部第三研究院第三设计部 | Angle measuring device for moveable wing surface of spacecraft |
| CN1811173A (en) * | 2006-02-15 | 2006-08-02 | 严强 | Attack angle regulator for vane of vertical shaft wind-driven generator |
| CN101963499A (en) * | 2010-07-21 | 2011-02-02 | 中国航空工业集团公司西安飞机设计研究所 | Tool and method for measuring deflection angle of airplane control surface |
| CN201867159U (en) * | 2010-09-29 | 2011-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Angle measuring mechanism for narrow left-side space |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1586951A1 (en) * | 1988-05-30 | 1990-08-23 | Предприятие П/Я Ю-9047 | Outboard device for ship for geophysical measurements |
-
2011
- 2011-08-15 CN CN201110232671.7A patent/CN102944207B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2035870U (en) * | 1988-09-29 | 1989-04-12 | 航天部第三研究院第三设计部 | Angle measuring device for moveable wing surface of spacecraft |
| CN1811173A (en) * | 2006-02-15 | 2006-08-02 | 严强 | Attack angle regulator for vane of vertical shaft wind-driven generator |
| CN101963499A (en) * | 2010-07-21 | 2011-02-02 | 中国航空工业集团公司西安飞机设计研究所 | Tool and method for measuring deflection angle of airplane control surface |
| CN201867159U (en) * | 2010-09-29 | 2011-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Angle measuring mechanism for narrow left-side space |
Non-Patent Citations (1)
| Title |
|---|
| 何森等: "标定飞机方向舵角位移的视觉测量法", 《光学工程》, vol. 36, no. 12, 31 December 2009 (2009-12-31), pages 73 - 78 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107764226A (en) * | 2017-11-09 | 2018-03-06 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of four angular displacement sensors layout drive mechanism |
| 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 |
| CN112461184A (en) * | 2020-11-10 | 2021-03-09 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102944207B (en) | 2015-04-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103308023B (en) | A kind of angle displacement measuring device and measuring method | |
| CN106769013B (en) | A kind of load inertia test apparatus of motor-driven cylinder | |
| CN102944207A (en) | Springback type angle displacement measurement device and measurement method thereof | |
| CN107202692B (en) | A kind of axial static rigidity of ball screw pair measuring device and method | |
| CN104875908A (en) | Cable-driven passive tensioning device of deployable mechanism | |
| CN104965129A (en) | Single-probe near-field antenna test system | |
| CN103994750A (en) | Three-axis stabilized platform angle detector for radar antenna and detection method thereof | |
| CN102607400A (en) | Precision spherical hinge clearance-measuring instrument and measurement method | |
| CN103511481B (en) | Rotation positioning device | |
| CN102778233B (en) | Horizontal framework locking device of aerial remote sensing inertially stabilized platform | |
| CN202547589U (en) | Precise ball hinge gap measuring instrument | |
| CN105806559A (en) | Device and method for measuring rotational inertia of satellite | |
| CN105547228A (en) | Angle displacement measurement device | |
| KR101015038B1 (en) | Apparatus for testing of actuator | |
| CN107966839B (en) | Multi-degree-of-freedom adjusting and detecting device for liquid crystal module | |
| CN102519671B (en) | Space position and gesture measuring device based on binocular vision and used for measuring gyroscope static balance | |
| CN105526904A (en) | Airplane control plane deflection angle measuring device | |
| CN107036795B (en) | Multifunctional debugging platform | |
| CN103134642B (en) | The five degree of freedom Butt sealing commissioning device of joint | |
| CN102519672B (en) | Monocular-principle-based six-degree-of-freedom position and attitude measuring device for measuring static balance of gyroscope | |
| CN202928535U (en) | Device for measuring gap between inner ring and outer ring of mounting joint between civil aviation aircraft engine and suspension arm | |
| CN103148989B (en) | The axial wobble device of joint tighness commissioning device | |
| CN106768904B (en) | A kind of helicopter ball flexible hub center piece Fatigue Testing Loads characterization and adjustment method | |
| CN210377146U (en) | Test tool for rudder servo controller | |
| CN208672815U (en) | A kind of position detecting mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |