CN108454882A - A kind of driving of rudder face and rudder face angle measuring mechanism - Google Patents
A kind of driving of rudder face and rudder face angle measuring mechanism Download PDFInfo
- Publication number
- CN108454882A CN108454882A CN201810305030.1A CN201810305030A CN108454882A CN 108454882 A CN108454882 A CN 108454882A CN 201810305030 A CN201810305030 A CN 201810305030A CN 108454882 A CN108454882 A CN 108454882A
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- rudder face
- arm
- axis
- bearing
- steering engine
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- 230000007246 mechanism Effects 0.000 title claims abstract description 39
- 230000007704 transition Effects 0.000 claims description 3
- 238000012360 testing method Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
Classifications
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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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/26—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes
Abstract
The invention discloses a kind of driving of rudder face and rudder face angle measuring mechanisms, solve the problems, such as that existing unmanned plane rudder plane controlling mechanism is unable to measure rudder face rotational angle, it include the hold-down support for placing steering engine and angular encoder, the rudder face being connect with steering engine, the hold-down support setting is fixed with bearing A and bearing B, setting is connected with drive mechanism between the steering engine and rudder face, the drive mechanism includes the rudder face axis being fixedly connected with rudder face, the shaft rotation arm being fixed on rudder face axis, with the steering engine arm of steering engine power output axis connection, the rocking arm of axis connection is rotated with angular encoder, it is hinged by connecting rod A between the steering engine arm and shaft rotation arm, it is hinged by connecting rod B between the rocking arm and shaft rotation arm, the rudder face axis sequentially passes through bearing B and bearing A, and rudder face axis is fixedly mounted on hold-down support.The rudder face of the present invention using the above structure drives and rudder face angle measuring mechanism, can not only rudder face be driven to rotate, while can also measure the angle of rudder face rotation.
Description
Technical field
The invention belongs to technical field of aerospace, and in particular to a kind of driving of rudder face and rudder face angle measuring mechanism.
Background technology
Model flight test is the one kind flown in an atmosphere by dummy vehicle and carry out aerodynamics Study on Problems
Simulated flight test method is one of three big research means of aerodynamics.Model in model flight test is usually basis
Fighter plane prototype size carries out a kind of unmanned plane after scaled down according to scale factor.
Control surface of the rudder face as aircraft, generally comprises elevator, rudder and aileron.Horizontal direction is elevator,
Namely horizontal tail is responsible for the pitching movement of control aircraft；Vertical direction is rudder, generally on vertical fin, is responsible for control
The yawing rotation of aircraft；Inclined direction makes aileron be responsible for the rolling movement of control aircraft generally in aircraft wing end.Mould
Type flight test needs the angle-data of rudder face rotation during acquisition unmanned plane during flying, but existing unmanned plane rudder face control machine
Structure is unable to measure rudder face rotational angle, it is therefore desirable to design a kind of driving of rudder face and rudder face angle measuring mechanism to solve rudder face angle
The measurement problem of degree.
Invention content
The present invention provides a kind of driving of rudder face and rudder face angle measuring mechanisms, solve existing unmanned plane rudder face control machine
Structure is unable to measure the problem of rudder face rotational angle, and steering engine delivers power to rudder face by drive mechanism and rudder face is driven to rotate,
Power is also transmitted to by angular encoder by drive mechanism simultaneously, the angle of rudder face rotation is measured by angular encoder.
The present invention to achieve the above object, is achieved through the following technical solutions：
A kind of driving of rudder face and rudder face angle measuring mechanism, include the hold-down support and rudder for placing steering engine and angular encoder
The rudder face of machine connection, the hold-down support setting are fixed with bearing A and bearing B, are arranged between the steering engine and rudder face and are connected with
Drive mechanism, the drive mechanism include the rudder face axis being fixedly connected with rudder face, the shaft rotation arm being fixed on rudder face axis and steering engine
The steering engine arm of power output axis connection, the rocking arm with angular encoder rotation axis connection, pass through between the steering engine arm and shaft rotation arm
Connecting rod A is hinged, and hinged by connecting rod B between the rocking arm and shaft rotation arm, the rudder face axis sequentially passes through bearing B and bearing
A, and rudder face axis is fixedly mounted on hold-down support.
In the above-mentioned technical solutions, the hold-down support includes bottom plate, setting in bottom plate both sides and vertical with bottom plate connects
Two support plates connect, the bottom plate are provided with rectangular through-hole.
In the above-mentioned technical solutions, described two support plates are each provided with a mounting hole, the bearing A and bearing B
In corresponding mounting hole.
In the above-mentioned technical solutions, the mounting hole is arranged along the axis direction of rudder face axis.
In the above-mentioned technical solutions, the shaft rotation arm includes the rotation axis being mounted on rudder face axis, fixes company with rotation axis
Two pivoted arms connect.
In the above-mentioned technical solutions, one end of pivoted arm and connecting rod B is hinged one of in described two pivoted arms, another
The other end of a pivoted arm and connecting rod A is hinged.
In the above-mentioned technical solutions, the other end of the connecting rod B and rocking arm are hinged, the other end of the connecting rod A with
Steering engine arm is hinged.
In the above-mentioned technical solutions, match for transition between the bearing A and hold-down support, between bearing B and hold-down support
It closes.
In the above-mentioned technical solutions, it is interference fit between the rudder face axis and bearing A, between rudder face axis and bearing B.
In conclusion by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
The present invention is compared with the mechanism of existing driving rudder face, and simple in structure, failure rate is low, and integrated level is high, and will cleverly drive
Motivation structure is connected with angular encoder design, this sampling device is not only able to driving rudder face rotation, while can measure rudder face
Rotational angle simplifies the test process of model flight test.
Description of the drawings
Fig. 1 is the overall structure diagram of the present invention.
Fig. 2 is the structural schematic diagram that the present invention omits hold-down support and rudder face.
Wherein：1, hold-down support, 2, rudder face, 3, steering engine, 4, steering engine arm, 5, connecting rod A, 6, shaft rotation arm, 7, bearing A, 8,
Rudder face axis, 9, bearing B, 10, connecting rod B, 11, rocking arm, 12, angular encoder.
Specific implementation mode
In order to make the purpose , technical scheme and advantage of the present invention be clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, and
It is not used in the restriction present invention.
A kind of rudder face driving as shown in Figure 1 and rudder face angle measuring mechanism, including hold-down support, steering engine, rudder face, angle volume
Code device and drive mechanism.Steering engine delivers power to rudder face by drive mechanism and rudder face is driven to rotate, while drive mechanism
Angular encoder is also delivered power to, the rotational angle of rudder face is measured by angular encoder.
Rudder face is located at hold-down support side, and rudder face is connect with steering engine by drive mechanism.Steering engine is that a kind of position is watched
Take driver or the driver of angle servo.
Angular encoder uses the absolute angular encoder of photo-electric, photo-electric absolute encoder to be equipped with encoder axis.
Hold-down support is for placing steering engine and angular encoder.Hold-down support includes bottom plate, is arranged in bottom plate both sides and bottom plate
The quantity of the support plate being mutually connected vertically, support plate is two and is each provided with one in the both sides of bottom plate.Two support plates
It is each provided with a mounting hole, mounting hole is adapted with bearing, and the mounting hole of one of support plate is installed with bearing
The mounting hole of A, another support plate are installed with bearing B.
Drive mechanism is used for transmission power.Drive mechanism setting is connected between steering engine and rudder face.As shown in Fig. 2, transmission
Structure includes rudder face axis, shaft rotation arm, steering engine arm, rocking arm and connecting rod.Rudder face axis is fixedly connected with rudder face and rudder face is with rudder face axis
It rotates together, rudder face axis is fixedly mounted on by sequentially passing through bearing B and bearing A on hold-down support, since mounting hole is along rudder face
The axis direction of axis is arranged, therefore bearing A and bearing B are also on the axis direction of rudder face axis.Shaft rotation arm is fixedly mounted on rudder face
It is rotated together on axis and with rudder face axis, shaft rotation arm is specifically arranged close to bearing A between bearing A and bearing B.Steering engine
The power output axis connection of arm and steering engine, steering engine arm include the rotation axis being mounted on rudder face axis, are fixedly connected with the rotating shaft
Two pivoted arms, wherein rotation axis drives rudder face axis to rotate together, and two pivoted arms are symmetrical arranged on the rotating shaft.Rocking arm is compiled with angle
The rotation axis connection of code device.Connecting rod includes connecting rod A and connecting rod B, is carried out by connecting rod A between steering engine arm and shaft rotation arm
It is hinged, it is hinged by connecting rod B between rocking arm and shaft rotation arm.Rudder face axis, shaft rotation arm, connecting rod B, rocking arm and angular encoder
It forms parallelogram and connects linkage.
The bottom plate of hold-down support is additionally provided with rectangular through-hole, drive mechanism at work steering engine arm, connecting rod A, shaft rotation arm,
The rotation amplitude of connecting rod B and rocking arm is larger, and rectangular through-hole and drive mechanism are adapted, make drive mechanism at work not by
Hold-down support influences.
Coordinate between bearing A and hold-down support, between bearing B and hold-down support for transition.Between rudder face axis and bearing A,
It is interference fit between rudder face axis and bearing B.
When mechanism drives rudder face rotation, steering engine, steering engine arm, connecting rod A, shaft rotation arm, rudder face axis and rudder face are sequentially connected.Tool
Body is that the power output shaft of steering engine is connect with steering engine arm one end, and the steering engine arm other end is hinged with the one end connecting rod A, and connecting rod A is another
One end connect with one of pivoted arm and then is connect with shaft rotation arm, and shaft rotation arm is mounted on rudder face axis, the front end of rudder face axis and axis
A connections are held, the rear end of rudder face axis is connect with rudder face.
Driving rudder face rotation process be：Steering engine power output shaft rotates and steering engine arm is driven to rotate, the steering engine arm of rotation
The rotation of shaft rotation arm is driven by connecting rod A, the shaft rotation armband of rotation moves rudder face axis and rudder face rotates together, that is, realizes driving rudder
The function of face rotation.
Mechanism measure rudder face rotational angle function when, steering engine, steering engine arm, connecting rod A, shaft rotation arm, rudder face axis and rudder face according to
While secondary connection, shaft rotation arm, connecting rod B, rocking arm are connected with angular encoder.Connection structure state when driving rudder face rotation
Under, while another pivoted arm and the one end connecting rod B are hinged, one end of the connecting rod B other ends and rocking arm is hinged, the other end of rocking arm
With the rotation axis connection of angular encoder.
Measure steering engine rotational angle process be：While driving rudder face rotation, the shaft rotation arm of rotation passes through connecting rod B
Rocking arm rotation, the rocking arm of rotation and the rotation axis connection of angular encoder, rudder face is driven to be rotated by the drive of shaft rotation arm, together
When shaft rotation armband shake arm rotation, therefore the rotational angle of rudder face is identical as the rotational angle of rocking arm, can pass through angular encoder
Directly measure the rotational angle of rudder face.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
All any modification, equivalent and improvement etc., should all be included in the protection scope of the present invention made by within refreshing and principle.
Claims (9)
1. a kind of driving of rudder face and rudder face angle measuring mechanism, it is characterised in that include for placing consolidating for steering engine and angular encoder
The rudder face determined bearing, connect with steering engine, the hold-down support setting is fixed with bearing A and bearing B, between the steering engine and rudder face
Setting is connected with drive mechanism, and the drive mechanism includes the rudder face axis being fixedly connected with rudder face, the axis being fixed on rudder face axis
Pivoted arm, the rocking arm with the steering engine arm of steering engine power output axis connection, with angular encoder rotation axis connection, the steering engine arm and shaft rotation
Hinged by connecting rod A between arm, hinged by connecting rod B between the rocking arm and shaft rotation arm, the rudder face axis sequentially passes through
Bearing B and bearing A, and rudder face axis is fixedly mounted on hold-down support.
2. a kind of rudder face driving according to claim 1 and rudder face angle measuring mechanism, it is characterised in that the fixed branch
Seat include bottom plate, setting bottom plate both sides and with bottom plate two support plates connected vertically, it is logical that the bottom plate is provided with rectangle
Hole.
3. a kind of rudder face driving according to claim 2 and rudder face angle measuring mechanism, it is characterised in that described two
Fagging is each provided with a mounting hole, and the bearing A and bearing B are mounted in corresponding mounting hole.
4. a kind of rudder face driving according to claim 3 and rudder face angle measuring mechanism, it is characterised in that the mounting hole
Axis direction along rudder face axis is arranged.
5. a kind of rudder face driving according to claim 1 and rudder face angle measuring mechanism, it is characterised in that the shaft rotation arm
Include rotation axis on rudder face axis, two pivoted arms being fixedly connected with the rotating shaft.
6. a kind of rudder face driving according to claim 5 and rudder face angle measuring mechanism, it is characterised in that described two turns
One end of pivoted arm and connecting rod B is hinged one of in arm, and the other end of another pivoted arm and connecting rod A is hinged.
7. a kind of rudder face driving according to claim 6 and rudder face angle measuring mechanism, it is characterised in that the connecting rod B
The other end and rocking arm it is hinged, the other end and steering engine arm of the connecting rod A is hinged.
8. a kind of rudder face driving according to claim 1 and rudder face angle measuring mechanism, it is characterised in that the bearing A and
Coordinate between hold-down support, between bearing B and hold-down support for transition.
9. a kind of rudder face driving according to claim 1 and rudder face angle measuring mechanism, it is characterised in that the rudder face axis
It is interference fit between bearing A, between rudder face axis and bearing B.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810305030.1A CN108454882B (en) | 2018-04-08 | 2018-04-08 | Control surface driving and control surface angle measuring mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810305030.1A CN108454882B (en) | 2018-04-08 | 2018-04-08 | Control surface driving and control surface angle measuring mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108454882A true CN108454882A (en) | 2018-08-28 |
| CN108454882B CN108454882B (en) | 2023-11-28 |
Family
ID=63234741
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810305030.1A Active CN108454882B (en) | 2018-04-08 | 2018-04-08 | Control surface driving and control surface angle measuring mechanism |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110487572A (en) * | 2019-07-30 | 2019-11-22 | 天利航空科技深圳有限公司 | Testing device of steering engine and steering engine test method |
| CN110553579A (en) * | 2019-10-10 | 2019-12-10 | 北京机械设备研究所 | electric steering engine based on four spatial connecting rods and method for measuring angle of rudder output shaft |
| 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 |
| CN110888459A (en) * | 2019-12-02 | 2020-03-17 | 中国空气动力研究与发展中心 | Vertical wind tunnel tail spin test model movable control surface deflection control mechanism |
| CN111891381A (en) * | 2020-06-17 | 2020-11-06 | 成都飞机工业（集团）有限责任公司 | Aircraft front wheel deflection angle measuring mechanism |
| CN112697389A (en) * | 2020-12-02 | 2021-04-23 | 哈尔滨工程大学 | Automatic angle changing device for closed-loop control surface and control method thereof |
| CN113008506A (en) * | 2021-02-19 | 2021-06-22 | 中国航天空气动力技术研究院 | Full-size large-load rudder wind tunnel unfolding test device |
| CN113640604A (en) * | 2021-08-12 | 2021-11-12 | 四川航天烽火伺服控制技术有限公司 | Comprehensive test device for electric steering engine |
| CN115384781A (en) * | 2022-06-20 | 2022-11-25 | 中国空气动力研究与发展中心空天技术研究所 | Reverse tail rotation device of aircraft and aircraft |
Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2114459A1 (en) * | 1971-03-25 | 1972-09-28 | Eppler, Richard, Prof. Dr., 7000 Stuttgart | Device for the storage of rudders and flaps of aircraft |
| JPH04138000U (en) * | 1991-06-20 | 1992-12-22 | 川崎重工業株式会社 | Aircraft control surface movement detector |
| JP2000335495A (en) * | 1999-05-31 | 2000-12-05 | Mitsubishi Heavy Ind Ltd | Control system of aircraft |
| CN101346276A (en) * | 2005-12-29 | 2009-01-14 | 空中客车德国有限公司 | Airfoil for an aircraft and aircraft |
| CN101508339A (en) * | 2008-12-24 | 2009-08-19 | 南京航空航天大学 | Directly connected-type direct current electric steering engine of rocker structure |
| US20100116929A1 (en) * | 2008-11-13 | 2010-05-13 | Honeywell International Inc. | Hybrid electromechanical/hydromechanical actuator and actuation control system |
| 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 |
| CN103308023A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Angle displacement measurement device and method |
| DE102012016093B3 (en) * | 2012-08-14 | 2014-02-13 | Mbda Deutschland Gmbh | Method for determining flight conditions and parameters of exit arrangement allowed for dropping external load from aircraft, involves executing test flights with different flight conditions and determining flight condition data |
| CN104290901A (en) * | 2014-10-20 | 2015-01-21 | 中国运载火箭技术研究院 | Double-rocker transmission mechanism applicable to movable control surface of aerial vehicle |
| CN104477378A (en) * | 2014-11-19 | 2015-04-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft longitudinal maneuvering limit limiting method and device thereof |
| CN104859848A (en) * | 2015-04-30 | 2015-08-26 | 中国科学院长春光学精密机械与物理研究所 | Front wheel steering mechanism suitable for unmanned aerial vehicle |
| CN105129074A (en) * | 2015-08-21 | 2015-12-09 | 湖北三江航天红峰控制有限公司 | Two-channel electric steering engine |
| CN205175383U (en) * | 2015-12-04 | 2016-04-20 | 张家港斯克斯精密机械科技有限公司 | Rotatory and angle of pitch measuring device of camera rocking arm |
| CA3063392A1 (en) * | 2014-10-31 | 2016-04-30 | The Boeing Company | Method for changing stiffness of a stiffness path in an aircraft structure |
| FR3031083A1 (en) * | 2014-12-31 | 2016-07-01 | Ratier Figeac Soc | ADJUSTABLE PALONNIER |
| CN106672207A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Middle-size unmanned aerial vehicle course control system |
| CN106882397A (en) * | 2017-02-01 | 2017-06-23 | 西安凯士电子科技有限公司 | Aircraft rudder surface deflects test device and method |
| CN207050700U (en) * | 2017-08-02 | 2018-02-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft rudder surface angle displacement measuring device |
| CN108100235A (en) * | 2017-11-22 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flap configuration control mechanism |
| CN208070050U (en) * | 2018-04-08 | 2018-11-09 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of driving of rudder face and rudder face angle measuring mechanism |
-
2018
- 2018-04-08 CN CN201810305030.1A patent/CN108454882B/en active Active
Patent Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2114459A1 (en) * | 1971-03-25 | 1972-09-28 | Eppler, Richard, Prof. Dr., 7000 Stuttgart | Device for the storage of rudders and flaps of aircraft |
| JPH04138000U (en) * | 1991-06-20 | 1992-12-22 | 川崎重工業株式会社 | Aircraft control surface movement detector |
| JP2000335495A (en) * | 1999-05-31 | 2000-12-05 | Mitsubishi Heavy Ind Ltd | Control system of aircraft |
| CN101346276A (en) * | 2005-12-29 | 2009-01-14 | 空中客车德国有限公司 | Airfoil for an aircraft and aircraft |
| US20100116929A1 (en) * | 2008-11-13 | 2010-05-13 | Honeywell International Inc. | Hybrid electromechanical/hydromechanical actuator and actuation control system |
| CN101508339A (en) * | 2008-12-24 | 2009-08-19 | 南京航空航天大学 | Directly connected-type direct current electric steering engine of rocker structure |
| 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 |
| DE102012016093B3 (en) * | 2012-08-14 | 2014-02-13 | Mbda Deutschland Gmbh | Method for determining flight conditions and parameters of exit arrangement allowed for dropping external load from aircraft, involves executing test flights with different flight conditions and determining flight condition data |
| CN103308023A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Angle displacement measurement device and method |
| CN104290901A (en) * | 2014-10-20 | 2015-01-21 | 中国运载火箭技术研究院 | Double-rocker transmission mechanism applicable to movable control surface of aerial vehicle |
| CA3063392A1 (en) * | 2014-10-31 | 2016-04-30 | The Boeing Company | Method for changing stiffness of a stiffness path in an aircraft structure |
| CN104477378A (en) * | 2014-11-19 | 2015-04-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft longitudinal maneuvering limit limiting method and device thereof |
| FR3031083A1 (en) * | 2014-12-31 | 2016-07-01 | Ratier Figeac Soc | ADJUSTABLE PALONNIER |
| CN104859848A (en) * | 2015-04-30 | 2015-08-26 | 中国科学院长春光学精密机械与物理研究所 | Front wheel steering mechanism suitable for unmanned aerial vehicle |
| CN105129074A (en) * | 2015-08-21 | 2015-12-09 | 湖北三江航天红峰控制有限公司 | Two-channel electric steering engine |
| CN205175383U (en) * | 2015-12-04 | 2016-04-20 | 张家港斯克斯精密机械科技有限公司 | Rotatory and angle of pitch measuring device of camera rocking arm |
| CN106672207A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Middle-size unmanned aerial vehicle course control system |
| CN106882397A (en) * | 2017-02-01 | 2017-06-23 | 西安凯士电子科技有限公司 | Aircraft rudder surface deflects test device and method |
| CN207050700U (en) * | 2017-08-02 | 2018-02-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft rudder surface angle displacement measuring device |
| CN108100235A (en) * | 2017-11-22 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flap configuration control mechanism |
| CN208070050U (en) * | 2018-04-08 | 2018-11-09 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of driving of rudder face and rudder face angle measuring mechanism |
Non-Patent Citations (2)
| Title |
|---|
| 汪培佩;: "一种可调的舵面位置测量系统", 科学技术创新, no. 20, pages 46 - 47 * |
| 王辉等: "风洞试验模型舵机系统研制", 实验流体力学, vol. 26, no. 3, pages 72 - 75 * |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110487572A (en) * | 2019-07-30 | 2019-11-22 | 天利航空科技深圳有限公司 | Testing device of steering engine and steering engine test method |
| CN110487572B (en) * | 2019-07-30 | 2022-08-23 | 天利航空科技深圳有限公司 | Steering engine testing device and steering engine testing method |
| CN110553579A (en) * | 2019-10-10 | 2019-12-10 | 北京机械设备研究所 | electric steering engine based on four spatial connecting rods and method for measuring angle of rudder output shaft |
| CN110888459A (en) * | 2019-12-02 | 2020-03-17 | 中国空气动力研究与发展中心 | Vertical wind tunnel tail spin test model movable control surface deflection control mechanism |
| 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 |
| CN111891381A (en) * | 2020-06-17 | 2020-11-06 | 成都飞机工业（集团）有限责任公司 | Aircraft front wheel deflection angle measuring mechanism |
| CN112697389A (en) * | 2020-12-02 | 2021-04-23 | 哈尔滨工程大学 | Automatic angle changing device for closed-loop control surface and control method thereof |
| CN113008506A (en) * | 2021-02-19 | 2021-06-22 | 中国航天空气动力技术研究院 | Full-size large-load rudder wind tunnel unfolding test device |
| CN113640604A (en) * | 2021-08-12 | 2021-11-12 | 四川航天烽火伺服控制技术有限公司 | Comprehensive test device for electric steering engine |
| CN115384781A (en) * | 2022-06-20 | 2022-11-25 | 中国空气动力研究与发展中心空天技术研究所 | Reverse tail rotation device of aircraft and aircraft |
| CN115384781B (en) * | 2022-06-20 | 2024-04-16 | 中国空气动力研究与发展中心空天技术研究所 | Anti-tail-spin device of aircraft and aircraft |
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