CN201623614U - Eddy current damper for airplane joystick control system - Google Patents
Eddy current damper for airplane joystick control system Download PDFInfo
- Publication number
- CN201623614U CN201623614U CN2009203504974U CN200920350497U CN201623614U CN 201623614 U CN201623614 U CN 201623614U CN 2009203504974 U CN2009203504974 U CN 2009203504974U CN 200920350497 U CN200920350497 U CN 200920350497U CN 201623614 U CN201623614 U CN 201623614U
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- damper
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- stator
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Abstract
The utility model belongs to the electromagnetism technology, and relates to improvement on a joystick system structure of an airplane joystick control system. An eddy current damper consists of a speed increaser (1), an electromagnetic damper (2) and a damping force adjusting apparatus (3), and is characterized in that the electromagnetic damper (2) comprises an outer stator (2a), a rotor (2b) and an inner stator (2c), wherein the rotor (2b) comprises a damper shaft (2b(1)) and a copper ring (2b(2)) bonded at the circumference of the damper shaft, the rotor (2b) is assembled in a bearing chamber of the inner stator (2c) through a bearing at one end of a rotating shaft, the outer stator (2a) is bonded on the inner wall of the damper, which corresponds to the outer surface of the rotor (2b), and the outer stator (2a) does not contact with the rotor (2b). The utility model has the advantages of small volume, light weight, compact structure, stable performance and capability of working under a severe environment.
Description
Technical field
The invention belongs to electromagnetic technique, relate to improvement aircraft control stick control system lever system structure.
Background technology
The artificial feel system of aircraft is second order concussion link, for the pitching that improves aircraft and the job stability of roll guidance, needs a damper in system, i.e. output and the proportional device of speed.All adopt hydraulic damper among traditional artificial feel system, but hydraulic damper have shortcomings such as damping force temperature influence, leakage of oil.Eddy-current damper is the damper that is produced damping force by electromagnetic principle, is used for the control stick vertical and horizontal damping action of having moved, and its volume is little, in light weight, compact conformation.
Summary of the invention
The objective of the invention is: propose that a kind of volume is little, in light weight, the electromagnetic type eddy-current damper of compact conformation, be applied to fly to control among the artificial feel system, realize damping action the motion of control stick vertical and horizontal.
Technical scheme of the present invention is: a kind of eddy-current damper that is used for the aircraft control stick control system, form by speed increaser, electromagnetic damper and damping force adjusting device three parts, it is characterized in that electromagnetic damper comprises external stator, rotor, internal stator, described rotor comprises damper shaft and is bonded in the copper cup of damper shaft excircle, rotor is assemblied in the bearing chamber of internal stator by an end bearing of rotating shaft, external stator be bonded in the corresponding damper inwall of rotor outer surface on, contactless between external stator and the rotor.
Operation principle of the present invention is to produce damping effect by the electromagnetic action principle, control stick links to each other with the power shaft of eddy-current damper with rocking arm by connecting rod, after the motion of control stick is quickened through gear speeder, driving the damping cup rotates in the magnetic field high speed that rare earth magnetic steel produces, the cutting electromotive force that produces on the damping cup that electric conducting material is made forms vortex flow, this vortex flow and the action of a magnetic field, produce and the proportional damping torque of rotating speed, the damping torque that is produced acts on the control stick after amplifying through speed increaser.The size of damping effect, adjustable by the damping coefficient adjusting device in desired scope internal linear.
Advantage of the present invention is: volume is little, in light weight, and compact conformation adopts the electromagnetic type technology, and through aircraft installation flight proof, properties of product are stable, can work under adverse circumstances.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is the outer stator structure schematic diagram;
Fig. 3 is a damping force adjusting device structural representation.
Embodiment
Below the present invention is described in further details.
Referring to Fig. 1, eddy-current damper is by speed increaser [1], electromagnetic damper [2] and damping force adjusting device [3] three parts are formed, electromagnetic damper [2] is the core of damper, comprise external stator [2a], rotor [2b], internal stator [2c], described rotor [2b] comprises damper shaft [2b (1)] and is bonded in the copper cup [2b (2)] of damper shaft excircle, rotor [2b] is assemblied in the bearing chamber of internal stator [2c] by an end bearing of rotating shaft, external stator [2a] be bonded in the corresponding damper inwall of rotor [2b] outer surface on, contactless between external stator [2a] and the rotor [2b], its gap is 0.23mm; When rotor [2b] rotates in the magnetic field high speed of being made up of magnet steel parts and internal stator [2c], in the copper cup of rotor [2b], form vortex flow, produce damping force; External stator [2a] is made up of magnet steel parts [2a (1)] and yoke [2a (2)], magnet steel parts [2a (1)] are adhered to yoke [2a (2)] inwall, magnet steel parts [2a (1)] are made up of four blocks of magnet steel [2a (1)-1] and magnet steel lining [2a (1)-2], and four blocks of magnet steel [2a (1)-1] evenly are bonded in four corresponding grooves of magnet steel lining [2a (1)-2] according to magnetic pole mode facing each other; Speed increaser [1] comprises front end housing [1a], input shaft gear [1b], tooth rest parts [1c] and Pyatyi gear drive [1d], front end housing [1a] by screw on the damper shell body, input shaft gear [1b] is connected with front end housing [1a] by bearing, tooth rest parts [1c] by screw on housing, Pyatyi gear drive [1d] is connected with tooth rest parts [1c] by bearing, input shaft gear [1b] and Pyatyi gear drive [1d] pass through gears engaged, on the tooth rest parts, ball bearing is installed, it is the optimal design of target function that Pyatyi gear drive [1d] and input shaft gear [1b] have adopted with the fastest ratio, all stressed member adopts high strength alloy steel simultaneously, the rotating speed of input shaft gear [1b] is delivered on the damper shaft by Pyatyi gear drive [1d] speedup, guarantees that damper has enough big output damping torque.Damping force adjusting device [3] is by internal stator pressing plate [3 (a)], bridge screw [3 (b)] and internal stator frame [3 (c)] are formed, internal stator pressing plate [3 (a)] is fixed on the internal stator frame [3 (c)] by bridge screw [3 (b)], can regulate damping force easily by changing the position of adjusting device in magnetic field, concrete grammar is for unscrewing bridge screw [3 (b)], can see evenly red green alternate each four round dot of distribution of circumferential end surfaces from the damper rear end, represent maximum damping coefficient position and minimum damping coefficient position respectively, regulate the position of internal stator frame [3 (c)] by special frock, thereby change the position of internal stator [2c] in magnetic field, play the effect of the size of regulating damping coefficient.
Eddy-current damper is a kind of device by electromagnetic action principle generation damping effect, and control stick links to each other with the power shaft of eddy-current damper with rocking arm by connecting rod.The power shaft that moves through eddy-current damper of control stick is after gear speeder quickens, driving the damping cup rotates in the magnetic field high speed that rare earth magnetic steel produces, the cutting electromotive force that produces on the damping cup that electric conducting material is made forms vortex flow, this vortex flow and the action of a magnetic field produce and the proportional damping torque of rotating speed, the damping torque that is produced acts on the control stick after amplifying through speed increaser, the size of damping effect, adjustable by the damping coefficient adjusting device in desired scope internal linear.The internal stator of damper is the magnetically soft alloy of high saturated magnetic induction, and has special shape, changes internal stator position in magnetic field, the size that can regulate damping coefficient easily.
Claims (4)
1. eddy-current damper that is used for the aircraft control stick control system, by speed increaser [1], electromagnetic damper [2] and damping force adjusting device [3] three parts are formed, it is characterized in that electromagnetic damper [2] comprises external stator [2a], rotor [2b], internal stator [2c], described rotor [2b] comprises damper shaft [2b (1)] and is bonded in the copper cup [2b (2)] of damper shaft excircle, rotor [2b] is assemblied in the bearing chamber of internal stator [2c] by an end bearing of rotating shaft, external stator [2a] be bonded in the corresponding damper inwall of rotor [2b] outer surface on, contactless between external stator [2a] and the rotor [2b].
2. according to the described eddy-current damper that is used for the aircraft control stick control system of claim 1, it is characterized in that, described speed increaser [1] comprises front end housing [1a], input shaft gear [1b], tooth rest parts [1c] and Pyatyi gear drive [1d], front end housing [1a] by screw on the damper shell body, input shaft gear [1b] is connected with front end housing [1a] by bearing, tooth rest parts [1c] by screw on housing, Pyatyi gear drive [1d] is connected with tooth rest parts [1c] by bearing, and input shaft gear [1b] and Pyatyi gear drive [1d] pass through gears engaged.
3. according to the described eddy-current damper that is used for the aircraft control stick control system of claim 1, it is characterized in that, described external stator [2a] is made up of magnet steel parts [2a (1)] and yoke [2a (2)], magnet steel parts [2a (1)] are adhered to yoke [2a (2)] inwall, described magnet steel parts [2a (1)] are made up of four blocks of magnet steel [2a (1)-1] and magnet steel lining [2a (1)-2], and four blocks of magnet steel [2a (1)-1] evenly are bonded in four corresponding grooves of magnet steel lining [2a (1)-2] according to magnetic pole mode facing each other.
4. according to the described eddy-current damper that is used for the aircraft control stick control system of claim 1, it is characterized in that, described damping force adjusting device [3] is made up of internal stator pressing plate [3 (a)], bridge screw [3 (b)] and internal stator frame [3 (c)], and internal stator pressing plate [3 (a)] is fixed on the internal stator frame [3 (c)] by bridge screw [3 (b)].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203504974U CN201623614U (en) | 2009-12-29 | 2009-12-29 | Eddy current damper for airplane joystick control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203504974U CN201623614U (en) | 2009-12-29 | 2009-12-29 | Eddy current damper for airplane joystick control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201623614U true CN201623614U (en) | 2010-11-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009203504974U Expired - Lifetime CN201623614U (en) | 2009-12-29 | 2009-12-29 | Eddy current damper for airplane joystick control system |
Country Status (1)
| Country | Link |
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| CN (1) | CN201623614U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102588544A (en) * | 2011-01-13 | 2012-07-18 | 珠海格力电器股份有限公司 | Air conditioner and magnetic damping rotation mechanism |
| CN105292500A (en) * | 2015-11-17 | 2016-02-03 | 江西洪都航空工业集团有限责任公司 | Compact type side rod control device based on man-machine working efficiency |
| WO2016091220A1 (en) * | 2014-12-12 | 2016-06-16 | 廖新春 | Acute angle magnetic damper |
| CN108622425A (en) * | 2018-05-07 | 2018-10-09 | 贵州华阳电工有限公司 | Electromagnetic damping operating mechanism |
| CN111022543A (en) * | 2019-12-24 | 2020-04-17 | 兰州飞行控制有限责任公司 | Electromagnetic damper based on permanent magnet brushless damping motor |
-
2009
- 2009-12-29 CN CN2009203504974U patent/CN201623614U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102588544A (en) * | 2011-01-13 | 2012-07-18 | 珠海格力电器股份有限公司 | Air conditioner and magnetic damping rotation mechanism |
| CN102588544B (en) * | 2011-01-13 | 2015-08-12 | 珠海格力电器股份有限公司 | Air conditioner and magnetic damping rotation mechanism |
| WO2016091220A1 (en) * | 2014-12-12 | 2016-06-16 | 廖新春 | Acute angle magnetic damper |
| CN105292500A (en) * | 2015-11-17 | 2016-02-03 | 江西洪都航空工业集团有限责任公司 | Compact type side rod control device based on man-machine working efficiency |
| CN108622425A (en) * | 2018-05-07 | 2018-10-09 | 贵州华阳电工有限公司 | Electromagnetic damping operating mechanism |
| CN111022543A (en) * | 2019-12-24 | 2020-04-17 | 兰州飞行控制有限责任公司 | Electromagnetic damper based on permanent magnet brushless damping motor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20101103 |
|
| CX01 | Expiry of patent term |