CN206476096U - A kind of light aerocraft Aileron control system - Google Patents
A kind of light aerocraft Aileron control system Download PDFInfo
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- CN206476096U CN206476096U CN201720051596.7U CN201720051596U CN206476096U CN 206476096 U CN206476096 U CN 206476096U CN 201720051596 U CN201720051596 U CN 201720051596U CN 206476096 U CN206476096 U CN 206476096U
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Abstract
The utility model discloses a kind of light aerocraft Aileron control system.Including left control crank device, right control crank device, port aileron torsion bar, starboard aileron torsion bar, aileron synchronizing bar, pushing-pulling flexible shaft, space four bar linkage mechanism, port aileron and starboard aileron, two pushing-pulling flexible shafts are arranged symmetrically, two spaces quadric chain is arranged symmetrically, small rod in left control crank device is connected with port aileron torsion bar, the port aileron torsion bar other end is connected with aileron synchronizing bar, flexible shaft end in aileron synchronizing bar is connected with pushing-pulling flexible shaft, the pushing-pulling flexible shaft other end is connected with space four bar linkage mechanism, the deflection of port aileron and starboard aileron can be driven by space four bar linkage mechanism, right control crank device can control port aileron and starboard aileron counter motion simultaneously with the either of which in left control crank device.The utility model is a kind of light aerocraft Aileron control system for ensureing aileron movement angle with high precision.
Description
Technical field
The utility model belongs to a kind of aircraft wing steerable system, more particularly to a kind of aircraft Aileron control system.
Background technology
Flight control system usually requires that manipulation is accurate and reliable and stable when designing.The aileron control system of traditional light aerocraft
System be mostly by push-and-pull cable wire or the direct primary control surface of connecting rod, with taking that aircraft space is big, idle stroke big, it is complicated to install,
The shortcomings of reliability is not high, it is difficult to meet the demand for development of light aerocraft Aileron control system.And pushing-pulling flexible shaft have it is extremely low
Friction, minimum idle stroke, tensile strength are high, bending radius is small and durable, compact, it is flexible the features such as, it is ensured that long distance
From the precision of transmission, minimum idle stroke can be still kept to be damaged with minimum strength in this long-distance transmission of Aileron control system
Lose, more preferable continuous running work makes the stability of Aileron control system be improved significantly.
Generally aileron motion is differential in addition, and it is inclined under it that part civil aircraft is often designed to that angle inclined on aileron is much larger than
Angle, its reason be on aileron partially when need larger deflection angle to meet pneumatic efficiency.Therefore a kind of satisfaction is found
The structure of the requirements such as fuselage and wing installing space are limited, drive path length and aileron differential motion, improves light aerocraft pair
Wing steerable system accuracy and reliability, it is significant.
The content of the invention
The problem of precision and not high transmission device reliability of aileron movement angle being manipulated for traditional Aileron control system,
The utility model provides a kind of light aerocraft Aileron control system for the accuracy and reliability for improving Aileron control system
The purpose of this utility model is achieved through the following technical solutions：
A kind of light aerocraft Aileron control system, including left control crank device, port aileron torsion bar, aileron synchronizing bar, push away
Flexible axle, space four bar linkage mechanism, port aileron and starboard aileron are drawn, the pushing-pulling flexible shaft has identical two and is arranged symmetrically, space
Quadric chain has identical two and is arranged symmetrically, wherein：One end of left control crank device and the port aileron torsion bar connects
Connect, the port aileron torsion bar other end is connected with aileron synchronizing bar, the one end of the two ends of aileron synchronizing bar respectively with two pushing-pulling flexible shafts
Connection, the one end of the other ends of two pushing-pulling flexible shafts respectively with two spaces quadric chain is connected, two spaces double leval jib machine
The other end of structure is connected with port aileron and starboard aileron respectively；Left control crank device can control port aileron and starboard aileron is simultaneously reverse
Motion.
Steerable system has used pushing-pulling flexible shaft in the utility model, pushing-pulling flexible shaft have can load strong pulling force and thrust, make
With need not be lubricated in the phase and adjust, high precision and position is repeated, service life length insensitive to temperature change and circulation
The features such as number of times is high, and pushing-pulling flexible shaft is combined with aerial quadric chain can improve the accurate of light aerocraft Aileron control system
Property and reliability, the occasion such as the wing space that is particularly suitable for use in is small, drive path length.
Further, light aerocraft includes is both provided with location wing on port wing and starboard wing, port wing and starboard wing
Rib, wing rear spar and wing girder, the positioning rib are arranged between wing rear spar and wing girder.
Further, pushing-pulling flexible shaft includes central shaft and shell two parts, the central shaft activity of the pushing-pulling flexible shaft
It is arranged in shell.
It is further preferred that pushing-pulling flexible shaft uses ball-type pushing-pulling flexible shaft.
Further, it is fixed with positioning rib on mounting seat, the light aerocraft fuselage and is provided with console connecting plate,
The console connecting plate two ends are fixed with locating piece, wherein：Pushing-pulling flexible shaft shell one end is connected by locating piece with console
Plate is connected, and the pushing-pulling flexible shaft shell other end is connected by mounting seat with positioning rib, the pushing-pulling flexible shaft central shaft
Input is connected with aileron synchronizing bar, and the output end of the pushing-pulling flexible shaft central shaft is connected with space four bar linkage mechanism.
Further, space four bar linkage mechanism includes double rocking arm, kinematic link and hinged-supports, and described pair of rocking arm is included actively
Rocking arm and from motion rocker arm, two spaces quadric chain is all connected by the pushing-pulling flexible shaft of initiatively rocking arm respectively corresponding thereto,
Described pair of rocking arm rotates around it axes O1Rotation can drive hinged-support to rotate, pivot center O1Direction is vertical with mounting seat, two
The space four bar linkage mechanism is connected with port aileron and starboard aileron respectively by hinged-support, and the hinged-support is rotatably fixed on
On wing rear spar, and rotate around it axes O2Rotation can make above and below port aileron and starboard aileron deflect.
Space four bar linkage mechanism is differential attachment, and its design principle is, by the installation initial positions of the double rocking arms of adjustment and
The size of each connecting rod can change the transmission direction and transmission ratios of double rocking arms, when left and right pair of rocking arm is obtaining equidirectional, position
When moving input, due to being arranged symmetrically, the direction of motion that is exported on left and right hinged-support is on the contrary, and output valve size not phase
Deng.
Further, left control crank device includes handle, bearing, cross axis body and small rod, and the cross axis body is erected
It is connected respectively with handle and small rod to two ends, the cross axis body transverse ends are connected with bearing, the bearing is consolidated with fuselage
Fixed connection, the left control crank device is connected by small rod with port aileron torsion bar.
Further, port aileron torsion bar includes preceding mounting seat, rear mounting seat, front-end bearing pedestal, rear bearing block and rotating bar, institute
Mounting seat is connected with front-end bearing pedestal before stating, and the rear mounting seat is connected with rear bearing block, the preceding mounting seat and rear mounting seat and
Fuselage is fixedly connected, and the rotating bar two ends are connected with the front-end bearing pedestal and rear bearing block respectively, front-end bearing pedestal and rear bearing
Bearing is fitted with seat, the rotating bar can be rotated around own axes, the two ends point that port aileron torsion bar passes through rotating bar
It is not connected with left control crank device and aileron synchronizing bar.
It is further preferred that rotating rod rear end is provided with the limited block for limiting its rotation amplitude, the rotation of rotating bar is prevented
Amplitude is excessive.
Further, aileron synchronizing bar connects including left spherical plain bearing rod end, synchronising (connecting) rod, left flexible shaft end and right flexible axle
Head, the aileron synchronizing bar is connected by left spherical plain bearing rod end with port aileron torsion bar, the left flexible shaft end, right flexible shaft end
The two ends of synchronising (connecting) rod are separately fixed at, the aileron synchronizing bar is pushed away with two respectively by left flexible shaft end and right flexible shaft end
Draw flexible axle connection.
Further, light aerocraft Aileron control system also includes right control crank device and starboard aileron torsion bar, the right side
Control crank device and starboard aileron torsion bar are identical with left control crank device and port aileron torsion bar, and are arranged symmetrically, the aileron
Synchronizing bar is provided with right spherical plain bearing rod end, and aileron synchronizing bar is connected by right spherical plain bearing rod end with starboard aileron torsion bar, described
Right control crank device can control port aileron and starboard aileron counter motion simultaneously with the either of which in left control crank device.
Transmission principle of the present utility model is as follows：
It can make to deflect above and below small rod by control crank, the deflection up and down of small rod drives port aileron torsion bar around itself
Axis is rotated；Port aileron torsion bar carries out rotation around own axes and drives aileron synchronizing bar to swing；Pushing-pulling flexible shaft center
Bar axle can carry out stretching motion, swinging for aileron synchronizing bar can be converted into the stretching motion of central shaft itself,
Double rocking arms of space four-linkses are driven around O by the stretching motion of central shaft itself1Axle is rotated, so as to drive the company of space four
The rotation of hinged-support in linkage, hinged-support is rigidly connected with aileron, is deflected so as to drive above and below port aileron and starboard aileron.
More specifically, when the handle in left control crank device or right control crank device is deflected to the left, driving left
Aileron is upward deflected, and starboard aileron is deflected down, when the handle in left control crank device or right control crank device is to right avertence
When turning, port aileron is driven to deflect down, starboard aileron is upward deflected.
Compared with the prior art, the beneficial effects of the utility model are：
The utility model aileron torsion bar is arranged in fuselage both sides, it is possible to increase fuselage interior space availability ratio；Using push-and-pull
Flexible axle combines transmission with space four bar linkage mechanism, wing space is small, the motion of drive path length, aileron be energy in the case of differential
It is enough realize precisely be driven and with higher reliability and it is easy to install the features such as；Using two control crank devices, right manipulation hand
Handle device can control port aileron and starboard aileron counter motion simultaneously with the either of which in left control crank device；This practicality is new
Type be it is a kind of with high precision ensure aileron movement angle steerable system, a kind of accuracy of raising Aileron control system with can
By the light aerocraft Aileron control system of property.
Brief description of the drawings
Fig. 1 is assembly structure diagram of the present utility model.
Fig. 2 is control crank device of the present utility model and aileron torsion bar assembly structure diagram.
Fig. 3 is the schematic diagram of mechanism of the utility model space four bar linkage mechanism.
Embodiment
The utility model embodiment accompanying drawing being given for example only property explanation, it is impossible to be interpreted as to limitation of the present utility model.For
More preferable explanation the present embodiment, some parts of accompanying drawing have omission, zoomed in or out, and do not represent the size of actual product；It is right
For those skilled in the art, some known features and its explanation may be omitted and will be understood by accompanying drawing.With reference to
Drawings and examples are described further to the technical solution of the utility model.
Embodiment
Referring to Fig. 1 to Fig. 2, the light aerocraft Aileron control system in the present embodiment includes left control crank device, right behaviour
Vertical handle apparatus, port aileron torsion bar 6, starboard aileron torsion bar 17, aileron synchronizing bar 11, pushing-pulling flexible shaft 13, space four bar linkage mechanism 18,
Port aileron 19 and starboard aileron 20, pushing-pulling flexible shaft 13 have identical two and are arranged symmetrically, and space four bar linkage mechanism 18 has identical
Two and it is arranged symmetrically, left control crank device is connected with one end of port aileron torsion bar 6, the other end of port aileron torsion bar 6 and aileron
Synchronizing bar 11 is connected, and the one end of the two ends of aileron synchronizing bar 11 respectively with 2 pushing-pulling flexible shafts 13 is connected, 2 pushing-pulling flexible shafts 13
The one end of the other end respectively with 2 space four bar linkage mechanisms 18 is connected, the other ends of 2 space four bar linkage mechanisms 18 respectively with
Port aileron 19 and starboard aileron 20 are connected；The function phase of right control crank device and left control crank device is same, two control cranks
Either of which in device can control port aileron and starboard aileron to move simultaneously.
Light aerocraft, which includes, is both provided with positioning rib 27, wing on port wing and starboard wing, port wing and starboard wing
The back rest 28 and wing girder 26, positioning rib 27 are arranged between wing rear spar 28 and wing girder 26.
Pushing-pulling flexible shaft 13 includes central shaft and shell two parts, and the central shaft of pushing-pulling flexible shaft 13 is movably arranged on shell
It is interior.
It is fixed with positioning rib 27 on mounting seat 25, light aerocraft fuselage and is provided with console connecting plate 15, console
The two ends of connecting plate 15 are fixed with locating piece 14, wherein：The shell one end of pushing-pulling flexible shaft 13 passes through locating piece 14 and console connecting plate
15 connections, the shell other end of pushing-pulling flexible shaft 13 is connected by mounting seat 25 with positioning rib 27, the central shaft of pushing-pulling flexible shaft 13
Two ends are connected with space four bar linkage mechanism 18 and aileron synchronizing bar 11 respectively.
Left control crank device and right control crank device all include handle 1, bearing 2, cross axis body 3 and small rod 7,
During installation, first handle 1 is connected with the one end of cross axis body 3, is then connected bearing 2 with the two ends of cross axis body 3, wherein cross axle
Body 3 is placed with copper sheathing and spacer in hole, is afterwards connected small rod 7 with the other end of cross axis body 3, finally by bearing 2 and fuselage
It is fixedly connected.
Port aileron torsion bar 6 and starboard aileron torsion bar 17 all include preceding mounting seat 4, rear mounting seat 9, front-end bearing pedestal 5, rear bearing block
8th, rotating bar 21 and limited block 10, the two ends of rotating bar 21 are connected with front-end bearing pedestal 5 and rear bearing block 8 respectively, and front-end bearing pedestal 5 is with after
Bearing block 8 is connected with preceding mounting seat 4 and rear mounting seat 9 respectively, and preceding mounting seat 4 and rear mounting seat 9 are fixedly connected with fuselage, wherein
A limited block 10 is welded with the rear end of rotating bar 21, for limiting the anglec of rotation of rotating bar 21.
Aileron synchronizing bar 11 includes left spherical plain bearing rod end 22, right spherical plain bearing rod end 24, synchronising (connecting) rod 23, left flexible axle and connect
First 12 and right flexible shaft end 16, left spherical plain bearing rod end 22 is bolted with aileron torsion bar 6, and left flexible shaft end 12 and the right side are soft
Shaft coupling 16 is fixed on synchronising (connecting) rod 23 two ends and the input with two pushing-pulling flexible shafts is bolted respectively.
Referring to Fig. 3, the output end of the initiatively rocking arm 32 and pushing-pulling flexible shaft 13 of double rocking arms in two spaces quadric chain 18
Hinged-support 31 in connection, two spaces quadric chain 18 is rigidly connected with port aileron 19 and starboard aileron 20 respectively, by pushing away
The elongation of the output end of flexible axle 13 is drawn to drive double rocking arms around axes O with shrinking1In A points rotate, it is logical from motion rocker arm 29 in double rocking arms
Cross kinematic link 30 and drive hinged-support 31 around axes O2In B points rotate, aileron movement can be driven by the deflection of hinged-support,
Wherein space four bar linkage mechanism 18 is differential attachment, and its design principle is, by the installation initial positions of the double rocking arms of adjustment and from
The size of motion rocker arm 29 and initiatively rocking arm 32 and kinematic link 30 can change the transmission direction and transmission ratios of double rocking arms, when two
Individual pair of rocking arm is when obtaining equidirectional, displacement input, due to being arranged symmetrically, the fortune exported on two hinged-supports 31
It is dynamic in opposite direction, and output valve size is unequal.
When the handle 1 of left control crank device is deflected to the left, the small rod 7 in left control crank device drives port aileron
Torsion bar 6 is around own axes rotate counterclockwise, when the handle 1 of left control crank device is deflected to the right, in left control crank device
Small rod 7 drive port aileron torsion bar 6 to be turned clockwise around own axes；
When port aileron torsion bar 6 is around own axes rotate counterclockwise, aileron synchronizing bar 11 is swung to the right, when port aileron is turned round
Bar 6 around own axes turn clockwise when, aileron synchronizing bar 11 is swung to the left side；
When aileron synchronizing bar 11 is swung to the right, the left input of pushing-pulling flexible shaft 13 is driven to shrink, output end elongation, simultaneously
Another right pushing-pulling flexible shaft input elongation is driven, output end is shunk；
Wherein, when the left output end of pushing-pulling flexible shaft 13 extends, double rocking arms in left space quadric chain 18 are around axes O1
In A points turn clockwise, so as to drive hinged-support 31 around axes O2In B points turn clockwise, and then drive port aileron 19
Upper inclined, another right pushing-pulling flexible shaft output end is shunk, and double rocking arms in right space quadric chain 18 are around axes O1In A points it is inverse
Hour hands rotate, so as to drive hinged-support 31 around axes O2In B point rotate counterclockwises, starboard aileron 20 times is partially；
I.e.：When the handle 1 in left control crank device is deflected to the left, port aileron 19 is driven to upward deflect, starboard aileron 20
Deflect down, when the handle 1 in left control crank device is deflected to the right, drive port aileron 19 deflect down, starboard aileron 20 to
Upper deflecting.
In order that multiple drivers can manipulate respectively, there are a right control crank device, right manipulation hand in the present embodiment
The function phase of handle device and left control crank device is same, and the either of which in two control crank devices can control port aileron simultaneously
With starboard aileron counter motion.Left control crank device is separately mounted to the driving cabin left and right sides with right control crank device, reduces
The interference of two pilot controls, convenient operation, while saving space.
Obviously, above-described embodiment is only intended to clearly illustrate the technical solution of the utility model example, and simultaneously
Non- is the restriction to embodiment of the present utility model.For those of ordinary skill in the field, in described above
On the basis of can also make other changes in different forms.There is no need and unable to give thoroughly all embodiments
Lift.All any modifications, equivalent substitutions and improvements made within spirit of the present utility model and principle etc., should be included in this
Within the protection domain of utility model right requirement.
Claims (10)
1. a kind of light aerocraft Aileron control system, it is characterised in that including left control crank device, port aileron torsion bar (6), pair
Wing synchronizing bar (11), pushing-pulling flexible shaft (13), space four bar linkage mechanism (18), port aileron (19) and starboard aileron (20), described in two
Pushing-pulling flexible shaft (13) is arranged symmetrically, and two space four bar linkage mechanisms (18) are arranged symmetrically, wherein：
The left control crank device is connected with one end of the port aileron torsion bar (6), port aileron torsion bar (6) other end with
The aileron synchronizing bar (11) connection, the two ends of the aileron synchronizing bar (11) are defeated with two pushing-pulling flexible shafts (13) respectively
Enter end connection, the one end of the output ends of two pushing-pulling flexible shafts (13) respectively with two spaces quadric chain (18) is connected,
The other end of two space four bar linkage mechanisms (18) is connected with port aileron (19) and starboard aileron (20) respectively；
The left control crank device can control port aileron (19) and starboard aileron (20) while counter motion.
2. light aerocraft Aileron control system according to claim 1, it is characterised in that the light aerocraft includes a left side
Positioning rib (27), wing rear spar (28) and wing girder (26) are both provided with wing and starboard wing, port wing and starboard wing,
The positioning rib (27) is arranged between wing rear spar (28) and wing girder (26).
3. light aerocraft Aileron control system according to claim 2, it is characterised in that the pushing-pulling flexible shaft (13) includes
Central shaft and shell two parts, the central shaft of the pushing-pulling flexible shaft (13) are movably arranged in shell.
4. light aerocraft Aileron control system according to claim 3, it is characterised in that solid on the positioning rib (27)
Surely have and console connecting plate (15) is provided with mounting seat (25), the light aerocraft fuselage, the console connecting plate (15)
Two ends are fixed with locating piece (14), wherein：
Described pushing-pulling flexible shaft (13) shell one end is connected by locating piece (14) with console connecting plate (15), the pushing-pulling flexible shaft
(13) the shell other end is connected by mounting seat (25) with positioning rib (27), the input of pushing-pulling flexible shaft (13) central shaft
End is connected with aileron synchronizing bar (11), and output end and the space four bar linkage mechanism (18) of pushing-pulling flexible shaft (13) central shaft connect
Connect.
5. light aerocraft Aileron control system according to claim 2, it is characterised in that the space four bar linkage mechanism
(18) double rocking arm, kinematic link (30) and hinged-supports (31) are included, described pair of rocking arm is including initiatively rocking arm (32) and from motion rocker arm
(29), pushing-pulling flexible shaft (13) of two space four bar linkage mechanisms (18) all by initiatively rocking arm (32) respectively corresponding thereto
Connection, described pair of rocking arm rotates around it axis (O1) rotate can drive hinged-support (31) rotate, two space four-linkses
Mechanism (18) is connected with port aileron (19) and starboard aileron (20) respectively by hinged-support (31), and the hinged-support (31) is rotatable
It is fixed on wing rear spar (28), and rotates around it axis (O2) rotation port aileron (19) and starboard aileron (20) can be made inclined up and down
Turn.
6. light aerocraft Aileron control system according to claim 1, it is characterised in that the left control crank device bag
Include handle (1), bearing (2), cross axis body (3) and small rod (7), the vertical two ends of the cross axis body (3) respectively with handle (1)
With small rod (7) connection, cross axis body (3) transverse ends are connected with bearing (2), and the bearing (2) is fixed with fuselage to be connected
Connect, the left control crank device is connected by small rod (7) with port aileron torsion bar (6).
7. light aerocraft Aileron control system according to claim 1, it is characterised in that port aileron torsion bar (6) bag
Include preceding mounting seat (4), rear mounting seat (9), front-end bearing pedestal (5), rear bearing block (8) and rotating bar (21), the preceding mounting seat (4)
It is connected with front-end bearing pedestal (5), the rear mounting seat (9) is connected with rear bearing block (8), the preceding mounting seat (4) and rear mounting seat
(9) be fixedly connected with fuselage, the rotating bar (21) can be rotated around own axes, rotating bar (21) two ends respectively with it is described
Bearing, the left secondary are fitted with front-end bearing pedestal (5) and rear bearing block (8) connection, front-end bearing pedestal (5) and rear bearing block (8)
Wing torsion bar (6) is connected with left control crank device and aileron synchronizing bar (11) respectively by the two ends of rotating bar (21).
8. light aerocraft Aileron control system according to claim 7, it is characterised in that rotating bar (21) rear end is set
It is equipped with the limited block (10) for limiting its rotation amplitude.
9. light aerocraft Aileron control system according to claim 1, it is characterised in that aileron synchronizing bar (11) bag
Left spherical plain bearing rod end (22), synchronising (connecting) rod (23), left flexible shaft end (12) and right flexible shaft end (16) are included, the aileron is synchronous
Bar (11) is connected by left spherical plain bearing rod end (22) with port aileron torsion bar (6), the left flexible shaft end (12), right flexible shaft end
(16) two ends of synchronising (connecting) rod (23) are separately fixed at, the aileron synchronizing bar (11) passes through left flexible shaft end (12) and right flexible axle
Joint (16) is connected with 2 pushing-pulling flexible shafts (13) respectively.
10. the light aerocraft Aileron control system according to claim 1 to 9 any one, it is characterised in that the aileron
Steerable system also includes right control crank device and starboard aileron torsion bar (17), right the control crank device and starboard aileron torsion bar
(17) it is identical with left control crank device and port aileron torsion bar (6), and be arranged symmetrically, the aileron synchronizing bar (11) is provided with the right side
Spherical plain bearing rod end (24), aileron synchronizing bar (11) is connected by right spherical plain bearing rod end (24) with starboard aileron torsion bar (17), institute
State right control crank device and can control port aileron (19) and starboard aileron (20) together with the either of which in left control crank device
When counter motion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720051596.7U CN206476096U (en) | 2017-01-17 | 2017-01-17 | A kind of light aerocraft Aileron control system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720051596.7U CN206476096U (en) | 2017-01-17 | 2017-01-17 | A kind of light aerocraft Aileron control system |
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| Publication Number | Publication Date |
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| CN206476096U true CN206476096U (en) | 2017-09-08 |
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| CN201720051596.7U Withdrawn - After Issue CN206476096U (en) | 2017-01-17 | 2017-01-17 | A kind of light aerocraft Aileron control system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107776873A (en) * | 2017-09-12 | 2018-03-09 | 陕西飞机工业（集团）有限公司 | A kind of aircraft aileron control mechanism |
| CN108313268A (en) * | 2017-01-17 | 2018-07-24 | 湖南山河科技股份有限公司 | A kind of light aerocraft Aileron control system |
| CN109720550A (en) * | 2018-11-12 | 2019-05-07 | 中航通飞研究院有限公司 | A kind of sidebar mechanism for purely mechanic flight control system |
| CN112623194A (en) * | 2020-12-22 | 2021-04-09 | 深圳墨菲航空科技有限公司 | Flaperon linkage system and aircraft |
| CN114013631A (en) * | 2021-11-19 | 2022-02-08 | 浙江省涡轮机械与推进系统研究院 | Fixed wing aircraft aileron control mechanism and fixed wing aircraft |
-
2017
- 2017-01-17 CN CN201720051596.7U patent/CN206476096U/en not_active Withdrawn - After Issue
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108313268A (en) * | 2017-01-17 | 2018-07-24 | 湖南山河科技股份有限公司 | A kind of light aerocraft Aileron control system |
| CN108313268B (en) * | 2017-01-17 | 2024-03-26 | 山河星航实业股份有限公司 | Aileron control system of light aircraft |
| CN107776873A (en) * | 2017-09-12 | 2018-03-09 | 陕西飞机工业（集团）有限公司 | A kind of aircraft aileron control mechanism |
| CN107776873B (en) * | 2017-09-12 | 2020-02-14 | 陕西飞机工业（集团）有限公司 | Aircraft aileron operating mechanism |
| CN109720550A (en) * | 2018-11-12 | 2019-05-07 | 中航通飞研究院有限公司 | A kind of sidebar mechanism for purely mechanic flight control system |
| CN109720550B (en) * | 2018-11-12 | 2023-09-19 | 中航通飞研究院有限公司 | Side lever mechanism for purely mechanical flight control system |
| CN112623194A (en) * | 2020-12-22 | 2021-04-09 | 深圳墨菲航空科技有限公司 | Flaperon linkage system and aircraft |
| CN114013631A (en) * | 2021-11-19 | 2022-02-08 | 浙江省涡轮机械与推进系统研究院 | Fixed wing aircraft aileron control mechanism and fixed wing aircraft |
| CN114013631B (en) * | 2021-11-19 | 2024-01-30 | 浙江省涡轮机械与推进系统研究院 | Aileron control mechanism of fixed-wing aircraft and fixed-wing aircraft |
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