CN105841605A - Quad redundant angular displacement sensor - Google Patents
Quad redundant angular displacement sensor Download PDFInfo
- Publication number
- CN105841605A CN105841605A CN201610262331.1A CN201610262331A CN105841605A CN 105841605 A CN105841605 A CN 105841605A CN 201610262331 A CN201610262331 A CN 201610262331A CN 105841605 A CN105841605 A CN 105841605A
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- CN
- China
- Prior art keywords
- angular displacement
- displacement sensor
- gear
- shaped housing
- sensor
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- 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.)
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
- G01B7/30—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapers; for testing the alignment of axes
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Length, Angles, Or The Like Using Electric Or Magnetic Means (AREA)
Abstract
The present invention provides a quad redundant angular displacement sensor. The sensor comprises a hollow U-shaped housing (2), the U-shaped housing (2) and a cover plate (3) are connected with each other through two screws to form the support structure of the whole sensor; a gear shaft (4) is installed on the U-shaped housing (2) and the cover plate (3) through inter-axis bearing (5) and a axis-end bearing (7), and the angular displacement sensors (9) of the four angular displacement sensor assemblies (1) are symmetrically installed at the bottom of the U-shaped housing (2) through a small pressing plate (8); and the gears (10) of the four angular displacement sensor assemblies (1) and anti-backlash gears (11) are symmetrically installed in the cavity of the U-shaped housing (2), and the gears (10) and the anti-backlash gears (11) re engaged with the gear of the gear shaft (4). The quad redundant angular displacement sensor is small in size, compact in structure, light in quality and high in reliability.
Description
Technical field
The present invention is a kind of four remaining angular displacement sensors, belongs to the technical field of structures of product.
Background technology
In order to meet the requirement to accelerator operating system of the aircraft fly-by-wire flight control system, along with the most electric
Sub-technology and the development of fax engine technology, the throttle platform of mechanical handling pattern will be gradually by fax
The throttle platform of operating pattern is substituted.Fax throttle platform can be effectively reduced the machine of Throttle Opening Control
Tool transmission link, alleviates weight, improves transmission accuracy, but is the biography realizing pilot control signal
Passing, fax accelerator mechanism generally uses angular displacement sensor to replace machine driving, carries for flight control system
For signal, it is achieved the control of engine throttle.
Owing to the reliable transmission ratio of single remaining angular displacement sensor is relatively low, for improving the reliable of system
Property, fax throttle platform necessarily uses redundant transducer to design.But, conventional redundance angular displacement
It is big to there is volume in sensor mechanical structure, and quality weight problem, use aboard is very limited.
Further, the performance of redundance angular displacement sensor except need to meet single channel angular displacement sensor performance want
Ask, also need to meet the conforming requirement of performance between remaining, and angular displacement sensor electric zero simultaneously
Position and the conforming requirement of mechanical zero, these are all to redundance angular displacement sensor frame for movement
Design, precision distribution and assembly technology are had higher requirement so that it is in fax throttle platform system
Use in system is restricted, and becomes one i.e. important problem demanding prompt solution again.
Summary of the invention
The present invention designs provide a kind of four positions, remaining angle for the deficiency of existing product existence just
Displacement sensor, its purpose is to solve usual redundance angular displacement sensor frame for movement volume big,
Quality weight, use occasion is limited, is not easy to the problem debug.
It is an object of the invention to be achieved through the following technical solutions:
This kind four remaining angular displacement sensor, it is characterised in that: this sensor includes four identical angles
Displacement sensor component (1), a kind of four remaining angular displacement sensor displacement sensor assemblies in each position, angle
(1) gear that the output shaft of an angular displacement sensor (9) and angular displacement sensor (9) connects is included
(10) clearance elimination gear (11) and with gear (10) being combined together；
This sensor also includes that the U-shaped housing (2) of a hollow, U-shaped housing (2) and cover plate (3) are logical
Crossing four screws and be joined together to form the supporting construction of whole sensor, gear shaft (4) passes through between centers
Bearing (5) and axle end bearing (7) are arranged on U-shaped housing (2) and cover plate (3), and four angular displacements pass
The angular displacement sensor (9) of sensor assembly (1) is symmetrically mounted on U-shaped housing (2) by little pressing plate (8)
Bottom, gear (10) and the clearance elimination gear (11) of four angular displacement sensor assemblies (1) are symmetrically installed
Gear phase at the intracavity of U-shaped housing (2), gear (10) and clearance elimination gear (11) with gear shaft (4)
Engagement.
This kind four remaining angular displacement sensor by the way of meshed transmission gear by the machine of gear shaft (4)
Tool input is transformed into magnitude of voltage, provides signal for flight control system, thus realizes engine oil gate control.
This kind four remaining angular displacement sensor volume is little, compact conformation, light weight, reliability high.Sensing
After device assembles, can effectively eliminate the transmission in Meshing Process of Spur Gear by clearance elimination gear (11)
Gap, improves the transmission accuracy of whole mechanism.Solve the most generally redundance angular displacement sensor
Frame for movement volume is big, and use occasion is limited, is not easy to the problem debug.
Accompanying drawing explanation
Fig. 1 is the structural representation of four remaining angular displacement sensors of the present invention
Fig. 2 is the structure of angular displacement sensor assembly in four remaining angular displacement sensors of the present invention
Signal
Fig. 3 be in Fig. 1 A to sectional view
Detailed description of the invention
Below with reference to drawings and Examples, the present invention is further described:
See shown in accompanying drawing 1～3, this kind four remaining angular displacement sensor, it is characterised in that: this biography
Sensor includes four identical angular displacement sensor assemblies (1), a kind of four positions, remaining angle, each position, angle
Displacement sensor displacement sensor assembly (1) includes an angular displacement sensor (9) and angular displacement sensor (9)
The gear (10) that connects of output shaft and the clearance elimination gear (11) that is combined together with gear (10)；
This sensor also includes that the U-shaped housing (2) of a hollow, U-shaped housing (2) and cover plate (3) are logical
Crossing four screws and be joined together to form the supporting construction of whole sensor, gear shaft (4) passes through between centers
Bearing (5) and axle end bearing (7) are arranged on U-shaped housing (2) and cover plate (3), and four angular displacements pass
The angular displacement sensor (9) of sensor assembly (1) is symmetrically mounted on U-shaped housing (2) by little pressing plate (8)
Bottom, gear (10) and the clearance elimination gear (11) of four angular displacement sensor assemblies (1) are symmetrically installed
Gear phase at the intracavity of U-shaped housing (2), gear (10) and clearance elimination gear (11) with gear shaft (4)
Engagement.
Gear shaft (4) in described four remaining angular displacement sensors passes through bearing pin and throttle lever mechanism phase
Even, driver can be rotated by pilot oil door rod driven gear axle (4), by the tooth of gear shaft (4)
Wheel engages with gear (10) and clearance elimination gear (11) gear of four angular displacement sensor assemblies (1), will
The machinery input of throttle platform is transformed into magnitude of voltage, passes to flight control system by electric connector,
After flight control system receives signal, the computing through signal is demarcated, and exports the signal of telecommunication by cable
Control accelerator operating device, it is achieved the control of engine throttle.
Claims (1)
1. a remaining angular displacement sensor, it is characterised in that: this sensor include four identical
Angular displacement sensor assembly (1), a kind of four remaining angular displacement sensor displacement sensors in each position, angle
Assembly (1) includes what the output shaft of an angular displacement sensor (9) and angular displacement sensor (9) connected
Gear (10) and the clearance elimination gear (11) being combined together with gear (10)；
This sensor also includes that the U-shaped housing (2) of a hollow, U-shaped housing (2) and cover plate (3) are logical
Crossing four screws and be joined together to form the supporting construction of whole sensor, gear shaft (4) passes through between centers
Bearing (5) and axle end bearing (7) are arranged on U-shaped housing (2) and cover plate (3), and four angular displacements pass
The angular displacement sensor (9) of sensor assembly (1) is symmetrically mounted on U-shaped housing (2) by little pressing plate (8)
Bottom, gear (10) and the clearance elimination gear (11) of four angular displacement sensor assemblies (1) are symmetrically installed
Gear phase at the intracavity of U-shaped housing (2), gear (10) and clearance elimination gear (11) with gear shaft (4)
Engagement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610262331.1A CN105841605A (en) | 2016-04-25 | 2016-04-25 | Quad redundant angular displacement sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610262331.1A CN105841605A (en) | 2016-04-25 | 2016-04-25 | Quad redundant angular displacement sensor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105841605A true CN105841605A (en) | 2016-08-10 |
Family
ID=56589046
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610262331.1A Pending CN105841605A (en) | 2016-04-25 | 2016-04-25 | Quad redundant angular displacement sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105841605A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107747932A (en) * | 2017-09-29 | 2018-03-02 | 兰州飞行控制有限责任公司 | A kind of rotary shaft position measurement apparatus of double remainings |
| CN108730425A (en) * | 2018-05-07 | 2018-11-02 | 西安航空制动科技有限公司 | A kind of planetary structure for wheel spin-up transducer |
| CN109373960A (en) * | 2018-12-05 | 2019-02-22 | 兰州飞行控制有限责任公司 | A kind of redundance angular displacement detecting device and installation method |
| CN109818455A (en) * | 2019-02-15 | 2019-05-28 | 湖北三江航天红峰控制有限公司 | A kind of parallel steering engine remaining angle feed-back system |
| CN112762816A (en) * | 2020-12-25 | 2021-05-07 | 兰州飞行控制有限责任公司 | Redundancy angular displacement sensor with self-isolation blocking fault and use method |
Citations (5)
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| US20070169357A1 (en) * | 2006-01-25 | 2007-07-26 | Kavlico Corp. | Multiple channel RVDT with dual load path and fail-safe mechanism |
| CN102565449A (en) * | 2012-01-05 | 2012-07-11 | 西安航空制动科技有限公司 | Double-section type four-redundancy airplane wheel velocity sensor |
| CN204255309U (en) * | 2014-11-14 | 2015-04-08 | 中国航空工业第六一八研究所 | The two remaining grating angular displacement sensor of a kind of Long Distances |
| CN104600901A (en) * | 2013-10-31 | 2015-05-06 | 北京精密机电控制设备研究所 | Four-redundant electromechanical servo mechanism |
| CN104697434A (en) * | 2013-12-10 | 2015-06-10 | 中国航空工业第六一八研究所 | Rotor zero-adjustment structure of double-redundancy angular displacement sensor and adjustment method of rotor zero-adjustment structure |
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2016
- 2016-04-25 CN CN201610262331.1A patent/CN105841605A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070169357A1 (en) * | 2006-01-25 | 2007-07-26 | Kavlico Corp. | Multiple channel RVDT with dual load path and fail-safe mechanism |
| CN102565449A (en) * | 2012-01-05 | 2012-07-11 | 西安航空制动科技有限公司 | Double-section type four-redundancy airplane wheel velocity sensor |
| CN104600901A (en) * | 2013-10-31 | 2015-05-06 | 北京精密机电控制设备研究所 | Four-redundant electromechanical servo mechanism |
| CN104697434A (en) * | 2013-12-10 | 2015-06-10 | 中国航空工业第六一八研究所 | Rotor zero-adjustment structure of double-redundancy angular displacement sensor and adjustment method of rotor zero-adjustment structure |
| CN204255309U (en) * | 2014-11-14 | 2015-04-08 | 中国航空工业第六一八研究所 | The two remaining grating angular displacement sensor of a kind of Long Distances |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107747932A (en) * | 2017-09-29 | 2018-03-02 | 兰州飞行控制有限责任公司 | A kind of rotary shaft position measurement apparatus of double remainings |
| CN108730425A (en) * | 2018-05-07 | 2018-11-02 | 西安航空制动科技有限公司 | A kind of planetary structure for wheel spin-up transducer |
| CN108730425B (en) * | 2018-05-07 | 2021-12-03 | 西安航空制动科技有限公司 | Planetary structure for airplane wheel speed sensor |
| CN109373960A (en) * | 2018-12-05 | 2019-02-22 | 兰州飞行控制有限责任公司 | A kind of redundance angular displacement detecting device and installation method |
| CN109373960B (en) * | 2018-12-05 | 2021-09-14 | 兰州飞行控制有限责任公司 | Redundancy angular displacement detection device and installation method |
| CN109818455A (en) * | 2019-02-15 | 2019-05-28 | 湖北三江航天红峰控制有限公司 | A kind of parallel steering engine remaining angle feed-back system |
| CN112762816A (en) * | 2020-12-25 | 2021-05-07 | 兰州飞行控制有限责任公司 | Redundancy angular displacement sensor with self-isolation blocking fault and use method |
| CN112762816B (en) * | 2020-12-25 | 2022-07-05 | 兰州飞行控制有限责任公司 | Redundancy angular displacement sensor with self-isolation blocking fault and use method |
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| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Ling Gang Inventor after: Guo Lili Inventor after: Xu Guoyu Inventor after: Xing Tiantian Inventor after: Cao Mengyu Inventor after: Liu Lei Inventor before: Ling Gang Inventor before: Guo Lili Inventor before: Xu Guoyu Inventor before: Xing Tiantian Inventor before: Cao Mengyu Inventor before: Liu Lei |
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| CB03 | Change of inventor or designer information | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160810 |
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| RJ01 | Rejection of invention patent application after publication |