CN104787356A - Rudder position adjusting and measuring clamp and method - Google Patents
Rudder position adjusting and measuring clamp and method Download PDFInfo
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- CN104787356A CN104787356A CN201510154698.7A CN201510154698A CN104787356A CN 104787356 A CN104787356 A CN 104787356A CN 201510154698 A CN201510154698 A CN 201510154698A CN 104787356 A CN104787356 A CN 104787356A
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- yaw rudder
- rudder
- adjustment
- yaw
- cusp
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Abstract
The invention provides a rudder position adjusting and measuring clamp and method. The clamp comprises a position pointer, clamping lug pieces and an elastic compressing device, wherein the position pointer is of a symmetrical structure; the outer contour projection of the position pointer is the same as that of the lower portion of an airplane rudder; the end of the position pointer is provided with a sharp point perpendicular to the horizontal datum of the clamp; the clamping lug pieces are symmetrically distributed on the two sides of the position pointer; the attachment surfaces are consistent with the appearance airplane wing surfaces. The clamp has wide portability and can almost be applied to adjustment and measurement of rudder systems of various airplanes.
Description
Technical field
The application relates to aircraft manufacturing assembly technique field, particularly a kind of yaw rudder position adjustment measured material and adjustment method of measurement thereof.
Background technology
In the flight course of aircraft, by deflecting of steer direction rudder system, influence air-flow thereon, thus change the stressed of aircraft, realize the yawing rotation of aircraft.Therefore the impact of order of accuarcy on flight safety of rudder system deflection is self-evident.
In the production process of aircraft, how effectively the deflection angle of control and measurement rudder system just seems necessity very.Because adjustment direction rudder kick angle need use yaw rudder itself as gauge reference target, and this benchmark is generally arranged on yaw rudder top, will carry out aloft work and there is very large risk when operating personal is measured, and brings great inconvenience for measuring.In order to avoid the risk that aloft work when measuring brings, way is in the past projected to same level at the measurement point of yaw rudder initial position and the measurement point after deflecting, and by measuring the distance between subpoint, calculates the angle of rudder kick.Due to the levelness impact of distortion and horizontal surface, the distance error of measurement several millimeter even more than, be difficult to the adjustment survey precision requirement meeting rudder of aircraft.
Summary of the invention
The object of the application there are provided a kind of yaw rudder position adjustment measured material, rudder of aircraft gauge reference target can be made to be transferred to bottom yaw rudder by yaw rudder top, and it is visible all the time in whole adjustment measurement process, avoid the risk that operating personal aloft work brings, measured error can be made to control within 0.5 millimeter of scope simultaneously.
A kind of yaw rudder position adjustment measured material, comprise position indicator pointer, clamping auricle and elastic pressuring clamping device, position indicator pointer is symmetrical structure, and the projection of its outline projects identical with rudder of aircraft bottom outline, position indicator pointer termination band one cusp, this cusp is perpendicular to fixture level reference; Clamping auricle is symmetrically distributed in position indicator pointer both sides, and its binding face is consistent with plane airfoil profile; Elastic pressuring clamping device is movably connected on clamping auricle.Elastic pressuring clamping device can adopt spiral to tighten compressing structure.
Following steps are taked to carry out when adjustment and direction of measurement rudder:
1, by yaw rudder mounting and adjusting bench mark from yaw rudder overhead projector to yaw rudder bottom, as yaw rudder bottom bench mark;
2, yaw rudder position adjustment measured material is placed in yaw rudder bottom, adjustment chucking position makes the cusp on position indicator pointer point overlap with yaw rudder bottom bench mark;
3, be fixed on yaw rudder with elastic pressuring clamping device by yaw rudder position adjustment measured material, installation process ensures that cusp overlaps with yaw rudder bottom bench mark all the time;
4, steering rudder system carries out angular deflection;
5, when yaw rudder moves to a certain position, the straight-line distance between ruler measurement cusp and yaw rudder bottom bench mark is used;
6, the deflection angle of continuous adjustment direction rudder, and constantly measure the straight-line distance between cusp and yaw rudder bottom bench mark, till this straight-line distance reaches in design nominal value dimension limit (also namely yaw rudder angular adjustment puts in place).
The advantage of the application has: measured material relies on the clamping of yaw rudder profile, without the need to by any assembly opening position on aircraft, can not cause any work of doing over again.Binding face and the aerofoil profile of elastic pressuring clamping device are coincide, and can avoid the damage to aerofoil in use procedure, also make the uniform force that is installed.This fixture has transplantability widely, and the adjustment that almost can be applied to the rudder system of all kinds of aircraft is measured.
Accompanying drawing explanation
Fig. 1 is yaw rudder position adjustment measured material birds-eye view;
Fig. 2 is yaw rudder position adjustment measured material front view;
Fig. 3 is yaw rudder position adjustment measured material parts I detail drawing.
Accompanying drawing illustrates: 1, position indicator pointer; 2, auricle is clamped; 3, elastic pressuring clamping device; 4, cusp
Detailed description of the invention
See accompanying drawing, a kind of yaw rudder position adjustment measured material, comprise position indicator pointer 1, clamping auricle 2 and elastic pressuring clamping device 3, position indicator pointer 1 is symmetrical structure, the projection of its outline projects identical with rudder of aircraft bottom outline, position indicator pointer 1 termination band one cusp 4, cusp 4 is perpendicular to fixture level reference; Clamping auricle 2 is symmetrically distributed in position indicator pointer 1 both sides, and its binding face is consistent with plane airfoil profile; Elastic pressuring clamping device 3 is movably connected on clamping auricle 2.Elastic pressuring clamping device 3 can adopt spiral to tighten compressing structure.Following steps are taked to carry out when adjustment and direction of measurement rudder:
1, by yaw rudder mounting and adjusting bench mark from yaw rudder overhead projector to yaw rudder bottom, as yaw rudder bottom bench mark;
2, yaw rudder position adjustment measured material is placed in yaw rudder bottom, adjustment chucking position makes the cusp 4 on position indicator pointer point 1 overlap with yaw rudder bottom bench mark;
3, be fixed on yaw rudder with elastic pressuring clamping device 3 by yaw rudder position adjustment measured material, installation process ensures that cusp 4 overlaps with yaw rudder bottom bench mark all the time;
4, steering rudder system carries out angular deflection;
5, when yaw rudder moves to a certain position, the straight-line distance between ruler measurement cusp 4 and yaw rudder bottom bench mark is used;
6, the deflection angle of continuous adjustment direction rudder, and constantly measure the straight-line distance between cusp 4 and yaw rudder bottom bench mark, till this straight-line distance reaches in design nominal value dimension limit (also namely yaw rudder angular adjustment puts in place).
Claims (3)
1. a yaw rudder position adjustment measured material and adjustment method of measurement, comprise position indicator pointer, clamping auricle and elastic pressuring clamping device, it is characterized in that described position indicator pointer is symmetrical structure, outline projection projects identical with rudder of aircraft bottom outline, described position indicator pointer termination band one cusp, this cusp is perpendicular to fixture level reference; Described clamping auricle is symmetrically distributed in position indicator pointer both sides, and its binding face is consistent with plane airfoil profile; Described elastic pressuring clamping device is movably connected on clamping auricle.
2. yaw rudder position adjusts measured material according to claim 1, it is characterized in that described elastic pressuring clamping device is that compressing structure tightened by spiral.
3. use the adjustment measured material of the yaw rudder position described in claim 1 to carry out rudder of aircraft adjusting the method measured, comprise the following steps:
1) by yaw rudder mounting and adjusting bench mark from yaw rudder overhead projector to yaw rudder bottom, as yaw rudder bottom bench mark;
2) yaw rudder position adjustment measured material is placed in yaw rudder bottom, adjustment chucking position makes the cusp on position indicator pointer point overlap with yaw rudder bottom bench mark;
3) be fixed on yaw rudder with elastic pressuring clamping device by yaw rudder position adjustment measured material, installation process ensures that cusp overlaps with yaw rudder bottom bench mark all the time;
4) steering rudder system carries out angular deflection;
5) when yaw rudder moves to a certain position, the straight-line distance between ruler measurement cusp and yaw rudder bottom bench mark is used;
6) deflection angle of continuous adjustment direction rudder, and constantly measure the straight-line distance between cusp and yaw rudder bottom bench mark, till this straight-line distance reaches in design nominal value dimension limit (also namely yaw rudder angular adjustment puts in place).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510154698.7A CN104787356B (en) | 2015-04-02 | 2015-04-02 | A kind of rudder position adjustment measuring method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510154698.7A CN104787356B (en) | 2015-04-02 | 2015-04-02 | A kind of rudder position adjustment measuring method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104787356A true CN104787356A (en) | 2015-07-22 |
| CN104787356B CN104787356B (en) | 2016-09-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510154698.7A Active CN104787356B (en) | 2015-04-02 | 2015-04-02 | A kind of rudder position adjustment measuring method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106864770A (en) * | 2017-02-24 | 2017-06-20 | 中国航天空气动力技术研究院 | It is a kind of to assess the method that unmanned plane manufactures the pneumatic deviation of profile |
| CN107651215A (en) * | 2017-10-19 | 2018-02-02 | 北京电子工程总体研究所 | A kind of inclined indicator alignment error compensation method of rudder |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU672475A1 (en) * | 1976-02-16 | 1979-07-05 | Предприятие П/Я А-7388 | Aircraft control turning angle monitor |
| CN2209324Y (en) * | 1994-03-10 | 1995-10-04 | 中国人民解放军空军驻3127厂军事代表 | Airplane rudder and adjusting sheet angle measuring device thereof |
| US20050044738A1 (en) * | 2003-08-26 | 2005-03-03 | John Adams | Digital inclinometer and related methods |
| 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 |
| CN204587333U (en) * | 2015-04-02 | 2015-08-26 | 中航飞机股份有限公司西安飞机分公司 | A kind of yaw rudder position adjustment measured material |
-
2015
- 2015-04-02 CN CN201510154698.7A patent/CN104787356B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU672475A1 (en) * | 1976-02-16 | 1979-07-05 | Предприятие П/Я А-7388 | Aircraft control turning angle monitor |
| CN2209324Y (en) * | 1994-03-10 | 1995-10-04 | 中国人民解放军空军驻3127厂军事代表 | Airplane rudder and adjusting sheet angle measuring device thereof |
| US20050044738A1 (en) * | 2003-08-26 | 2005-03-03 | John Adams | Digital inclinometer and related methods |
| 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 |
| CN204587333U (en) * | 2015-04-02 | 2015-08-26 | 中航飞机股份有限公司西安飞机分公司 | A kind of yaw rudder position adjustment measured material |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106864770A (en) * | 2017-02-24 | 2017-06-20 | 中国航天空气动力技术研究院 | It is a kind of to assess the method that unmanned plane manufactures the pneumatic deviation of profile |
| CN106864770B (en) * | 2017-02-24 | 2019-07-12 | 中国航天空气动力技术研究院 | A method of assessment unmanned plane manufactures the pneumatic deviation of shape |
| CN107651215A (en) * | 2017-10-19 | 2018-02-02 | 北京电子工程总体研究所 | A kind of inclined indicator alignment error compensation method of rudder |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104787356B (en) | 2016-09-14 |
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Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
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| TR01 | Transfer of patent right |
Effective date of registration: 20210617 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |