CN106314761B - A kind of all-moving wing mechanism applied to small compound helicopter - Google Patents
A kind of all-moving wing mechanism applied to small compound helicopter Download PDFInfo
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- CN106314761B CN106314761B CN201610791922.8A CN201610791922A CN106314761B CN 106314761 B CN106314761 B CN 106314761B CN 201610791922 A CN201610791922 A CN 201610791922A CN 106314761 B CN106314761 B CN 106314761B
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- wing
- moveable hinge
- starboard
- small compound
- moving
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/385—Variable incidence wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The present invention provides a kind of all-moving wing mechanism applied to small compound helicopter, including port wing and starboard wing；It is characterized in that：It further include wing girder, moveable hinge, fixed beam and control link mechanism.The port wing and starboard wing are symmetrically disposed on fuselage two sides, and inside is mounted on the wing girder extended to setting.Moveable hinge is two, is made up of both pitch change axes and moveable hinge shell bearing internal external socket, forms revolute pair.Above-mentioned two moveable hinge is respectively intended to realize the connection between port wing, starboard wing and fixed beam between end.Fixed beam middle section is installed on fuselage interior bracket.Two moveable hinges realize rotation of the moveable hinge shell with respect to pitch change axes respectively by a set of control link mechanism controls, and then make port wing and starboard wing around the rotation of wing girder axis, realize the angle of attack change of port wing and starboard wing.Advantages of the present invention is：Solve the problems, such as that small compound helicopter airfoil member reduces hovering performance, increases interference drag.
Description
Technical field
The invention belongs to technical field of aerospace, more particularly to a kind of all-moving wing applied to small compound helicopter
Mechanism.
Background technique
Composite helicopter is given birth to pursue speed.Say in general sense composite helicopter be by fixed-wing component with
Helicopter layout combines, and conventional composite formula layout is to increase auxiliary lifting system and augmented thrust system on pure helicopter
System, auxiliary lifting system is wing, and augmented thrust system is thrust propeller or thrust ducted fan.Classical combined type is straight
The machine of liter layout is comprising composite wing system (sharing rotor lift) and is installed on the propulsion system of tail portion and (provides additional advance to push away
Power)；
Composite helicopter has many advantages, first its speed limit that breaches pure helicopter, due to its rotor
It being unloaded, helicopter vibration level is lower, since wherein high speed pneumatic is high-efficient, voyage and endurance are increased, and because of its increase
Lift thrust auxiliary system, the mobility of aircraft are also promoted.But there are also disadvantages for composite helicopter, due to its increase
Auxiliary lifting and push system, system-wide weight increased, additionally, due to the mutual aerodynamic interference between each system, especially
It is the mutual aerodynamic interference between rotor and wing, so that composite helicopter hovering efficiency is lower than conventional type helicopter.Simultaneously
Composite wing increases the difficulty that helicopter enters spin states, declines the autorotative glide ability of aircraft, safety damages.
For composite helicopter, wing had not only been to provide the important component of lift unloading rotor, but also was hovering with before
Main interference source when flying.This aerodynamic loss is especially obvious when hovering, because the power that before flies when hovering, wing without
Pneumatic effect lays flat close to plate and acts on, and stops purling, is huge sources of resistance, reduces hovering efficiency, it is straight to influence combined type
Performance of the machine of liter in hovering.Existing composite helicopter speed hawk selection, by 90 degree of the aileron bottom, reduces hovering in hovering
Loss, and aileron area is very big, reduces the drawbacks of wing is in hovering as far as possible.But still there is lost area in this way.If adopting
With complete dynamic aerofoil, this has complete dynamic realization in fixed-wing horizontal tail, reduces by a rudder face and does full empennage movement, provides rudder inclined torque.
Fixed wing aircraft airfoil member has no complete and moves application to remove aileron structure, not due to its structural strength bring weight issue
It is cost-effective.Helicopter breaks down when preceding winged, need to enter spin situation, and wing is an obstruction component again, and rotor will be hindered to enter
Autorotation.The winged transition stage before composite helicopter hovering turns, the variation of fuselage attitude angle are in the fixed wing angle of attack
Nonideality, performance are bad.
Summary of the invention
In order to overcome the above-mentioned deficiencies of the prior art, the present invention provides a kind of applied to the complete dynamic of small compound helicopter
Wing structure, to solve the problems, such as that small compound helicopter airfoil member reduces hovering performance, increase interference drag.Full motivation
The wing casts out aileron component, can be directed to different flight state, change the wing angle of attack, be at wing under each mission phase optimal
Angle of attack position, while rudder face operating torque being provided, mitigate rotor control burden, (engine cut-off, rotor are unpowered in specific fault
Rotation) in the case of reduce the adverse effect that becomes a mandarin for rotor of wing.
The present invention is applied to the all-moving wing mechanism of small compound helicopter, and one kind being applied to small compound helicopter
All-moving wing mechanism, including port wing, starboard wing, wing girder, moveable hinge, fixed beam and control link mechanism.
The port wing and starboard wing are symmetrically disposed on fuselage two sides, and inside is mounted on the wing master extended to setting
Beam.Moveable hinge is two, is made up of both pitch change axes and moveable hinge shell bearing internal external socket, forms revolute pair.
Above-mentioned two moveable hinge is respectively intended to realize the connection between port wing, starboard wing and fixed beam between end；Fixed beam
Middle section is installed on fuselage interior bracket.Two moveable hinges respectively by a set of control link mechanism controls, realize moveable hinge shell
Relative to the rotation of pitch change axes, and then make port wing and starboard wing around the rotation of wing girder axis, realizes port wing and starboard wing
The angle of attack change.
The advantage of the invention is that：
1, the present invention is applied to the all-moving wing mechanism of small compound helicopter, solves composite helicopter in multiplexing
When condition flight, the fixed bring adverse effect of the wing angle of attack；
2, the present invention is applied to the all-moving wing mechanism of small compound helicopter, and structure is simple, can be applied to small-sized (total
Weight about 200kg or less) composite helicopter；
3, the present invention is applied to the all-moving wing mechanism of small compound helicopter, the wing in composite helicopter hovering
Vertically, reduce the adverse effect to hovering efficiency, improve full machine pneumatic efficiency；It flies over and tides over before composite helicopter hovering turns
Cheng Zhong, the not random body attitude angle of the all-moving wing angle of attack change, can preferably adapt to transient process, accelerate transitioning processes, reduce
Power loss improves final flying speed；When flying before composite helicopter is stablized, all-moving wing mechanism operating airfoil water
It is flat, the angle of attack, and the differential control angle of attack are finely tuned according to air-flow, it is possible to provide the equivalent rolling moment with fixed-wing wing aileron；?
When composite helicopter is eager to slow down, wing can tune to vertical position and provide flaps effect, when there is accident in helicopter,
Rotatable get out of the way of wing becomes a mandarin, and reduces wing and rotor is hindered to become a mandarin into the difficulty of spin.
Detailed description of the invention
Fig. 1 is all-moving wing mechanism structure schematic diagram of the present invention；
Fig. 2 is moveable hinge and its connected mode schematic diagram in all-moving wing mechanism of the present invention；
Fig. 3 is control link structural scheme of mechanism when flying before helicopter in all-moving wing mechanism of the present invention；
When Fig. 4 is helicopter hovering in all-moving wing mechanism of the present invention, control link structural scheme of mechanism；
Fig. 5 is status diagram when all-moving wing mechanism of the present invention flies before helicopter；
Fig. 6 is status diagram of the all-moving wing mechanism of the present invention when helicopter hovers.
In figure：
1- port wing 2- starboard wing 3- wing girder
4- moveable hinge 5- fixed beam 6- control link mechanism
7- fuselage 8- limited block 401- moveable hinge shell
The front 402- bearing sleeve 403- pitch change axes 404- rolling bearing
The rear portion 405- rolling bearing 406- top cover 601- steering engine
602- steering engine rocker arm 603- rocker-arm link 604- distance-variable rocker arm
Specific embodiment
Present invention will be further explained below with reference to the attached drawings and examples.
All-moving wing mechanism of the present invention includes the composite helicopter being applied to, wing and its company to composite helicopter
The mode of connecing improves, including port wing 1, starboard wing 2, wing girder 3, moveable hinge 4, fixed beam 5 and control link mechanism 6,
As shown in Figure 1.
The port wing 1 is symmetrically disposed on 7 left and right sides of fuselage with starboard wing 2, and inside, which is mounted on, to be extended to setting
Wing girder 3；In conjunction with comprehensively considering for aerodynamic moment and structural strength, in the present invention chordwise location of wing girder 3 be located at away from
The position of 30% chord length length of wing chord length leading edge, and between wing aerodynamic focus and maximum gauge.Port wing 1 and right machine
3 end of wing girder on the wing 2 is equipped with moveable hinge 4 using same way, and by moveable hinge 4 respectively with 5 both ends of fixed beam
It is connected.
The moveable hinge 4 includes moveable hinge shell 401, bearing sleeve 402 and pitch change axes 403, as shown in Figure 2；Wherein, living
Dynamic hinge 401 forward end of shell design has cylindric connecting pin, is inserted into the slot of 3 end coaxial design of wing girder, passes through
It is glued and fixes.Pitch change axes 403 and moveable hinge shell 401 are coaxially disposed, and front is located in moveable hinge shell 401, pass through moveable hinge
Two rolling bearings being axially arranged in shell 401 be connected with moveable hinge shell 401, it can be achieved that moveable hinge shell 401 it is smooth
It rolls.403 end of pitch change axes is inserted into the cylinder-like structure of 5 end of fixed beam design, realizes displacement through bolt by side wall
Axis 403 and fixed beam 5 are fixed.Enabling above-mentioned two rolling bearing is respectively front rolling bearing 404 and end rolling bearing 405,
Then front rolling bearing 404 and the mounting means of rear portion rolling bearing 405 are：Rolling bearing 404 outer ring in front passes through moveable hinge
The locating shoulder of 401 inner wall of shell design, realizes forward location；Rolling bearing 405 outer ring in end passes through moveable hinge casing ends
On annular gasket, to positioning after realization；It is opposite between 404 outer ring of front rolling bearing and end housing washer 405
Positioning is realized by covering the bearing sleeve 402 in pitch change axes 403.Rolling bearing 404 inner ring in front passes through coaxially solid by bolt
The top cover 406 being scheduled on 403 front end face of pitch change axes realizes forward location；404 inner ring of front rolling bearing and end rolling bearing
Relative positioning between 405 inner rings is realized by the annular convex platform designed in 403 circumferential direction of pitch change axes；While the annular convex platform is also
Realize the forward location of 405 inner ring of end rolling bearing；The backward positioning of 405 inner ring of end rolling bearing, passes through fixed beam 5
The annular end face of end is realized.From there through the rolling of two moveable hinge shells 401 of control, port wing 1 and the right side can be realized
The angle of attack of wing 2 changes, and port wing 1 and the discriminable flexible change angle of attack of starboard wing 2, realize all-moving wing change in angle of attack and
Differential rolling.
It is designed as beam type structure in the middle part of above-mentioned fixed beam 5, is bolted the mounting bracket being installed on inside fuselage 7
On, and yielding rubber pad is provided between fixed beam 5 and mounting bracket；It is realized between all-moving wing and fuselage 7 of the present invention with this
Installation is fixed.Above-mentioned all-moving wing is installed on 7 upper position of fuselage, reduces rotor and wing aerodynamic interferes；All-moving wing simultaneously
It is also needed to meet between fuselage 7：The pneumatic focus and 7 center of gravity of fuselage of all-moving wing are respectively positioned in front of rotor shaft, close to rotor shaft, and
On straight line of the same perpendicular to horizontal plane.
The control of above-mentioned port wing 1 and the change angle of attack of starboard wing 2, is realized by a set of control link mechanism 6 respectively.Manipulation
Link mechanism 6 includes steering engine 601, steering engine rocker arm 602, rocker-arm link 603 and distance-variable rocker arm 604, as shown in Figure 3, Figure 4.Wherein,
The input terminal of steering engine rocker arm 602 and 601 output shaft fixed connection of steering engine pass through Minisize axial between 603 input terminal of output end and rocker-arm link
Hold connected, 603 output end of rocker-arm link is connected by miniature bearing with 604 input terminal of distance-variable rocker arm；The output of distance-variable rocker arm 604
End is fixed with moveable hinge shell 401；And then it can be by steering engine rocker arm 602, rocker-arm link 603, distance-variable rocker arm 604 and steering engine rocker arm
It is considered as a four-bar mechanism between the pivot center line of 604 output end of 602 input terminals and distance-variable rocker arm；Wherein steering engine shakes
Arm 602, rocker-arm link 603 and 604 three's length ratio of distance-variable rocker arm are 30:26:45.Thus port wing 1 and starboard wing 2 pass through behaviour
Angle change in 120 degree of 601 output shaft of steering engine can be converted to port wing 1 by vertical connecting rod mechanism and 90 degree of starboard wing 2 vertical
The angle of attack variation that state is spent to -20, as shown in Figure 5, Figure 6；And by designing two limited blocks, limitation on 5 outer wall of fixed beam
The slewing area of distance-variable rocker arm 604, and then port wing 1 and 2 angle of attack variation of starboard wing are limited beyond steering range, i.e., -20 degree
To 90 degree, avoiding aerodynamic force burst effect causes the wing angle of attack to outrange injury of the variation range to control link mechanism.
It is the reduction of maximum possible using the composite helicopter of all-moving wing mechanism of the present invention when being in floating state
Interference controls port wing 1 by control link mechanism 6 and starboard wing 2 is in 90 degree of vertical states, as shown in Figure 5；Pass through behaviour
Vertical connecting rod mechanism 6 controls wing and air velocity is answered to change, and is gradually deflected to horizontality, makes composite helicopter by floating state
Winged state before stablizing is transitted to, port wing 1 and starboard wing 2 are in horizontality at this time, and there can be positive and negative 20 degree of the angle of attack to become
Change range, as shown in fig. 6, port wing 1 and starboard wing 2 thus can be allowed to avoid the adverse effect of 7 attitude angle of fuselage variation, and passes through
Differential control can provide the operating torque for being equivalent to aileron rolling.When composite helicopter is eager to slow down, wing be can tune to
Vertical position state, it is possible to provide should flight demand flap effect.When accident occurs in composite helicopter, connected by manipulation
Linkage 6 controls the rotation of port wing 1 and starboard wing 2, gets out of the way and becomes a mandarin, and reduces port wing 1 and hinders rotor to enter to flow into starboard wing 2
Enter the difficulty of spin.
Claims (8)
1. a kind of all-moving wing mechanism applied to small compound helicopter, including port wing and starboard wing；It is characterized in that：
It further include wing girder, moveable hinge, fixed beam and control link mechanism；
The port wing and starboard wing are symmetrically disposed on fuselage two sides, and inside is mounted on the wing girder extended to setting；It is living
Dynamic hinge is two, is made up of both pitch change axes and moveable hinge shell bearing internal external socket, forms revolute pair；
Above-mentioned two moveable hinge is respectively intended to realize the connection between port wing, starboard wing and fixed beam between end；Fixed beam middle section
It is installed on fuselage interior bracket；Two moveable hinges realize that moveable hinge shell is opposite respectively by a set of control link mechanism controls
Attacking for port wing and starboard wing is realized in the rotation of pitch change axes, and then make port wing and starboard wing around the rotation of wing girder axis
Angle changes；The design of moveable hinge case nose end has cylindric connecting pin, is inserted into the slot of wing girder end coaxial design,
It is fixed by being glued, displacement shaft end is inserted into the cylinder-like structure of fixed beam end design, is realized by side wall through bolt
Pitch change axes are fixed with fixed beam.
2. a kind of all-moving wing mechanism applied to small compound helicopter as described in claim 1, it is characterised in that：Wing
The chordwise location of girder is located at the position away from 30% chord length length of wing chord length leading edge, and thick between wing aerodynamic focus and maximum
Between degree.
3. a kind of all-moving wing mechanism applied to small compound helicopter as described in claim 1, it is characterised in that：It is fixed
Yielding rubber pad is provided between beam and mounting bracket.
4. a kind of all-moving wing mechanism applied to small compound helicopter as described in claim 1, it is characterised in that：Installation
In fuselage upper position；It needs to meet simultaneously：The pneumatic focus and body nodal point of all-moving wing are respectively positioned in front of rotor shaft, close to rotation
Wing axis, and it is located at same perpendicular on the straight line of horizontal plane.
5. a kind of all-moving wing mechanism applied to small compound helicopter as described in claim 1, it is characterised in that：Manipulation
Link mechanism includes steering engine, steering engine rocker arm, rocker-arm link and distance-variable rocker arm；Wherein, the input terminal of steering engine rocker arm and steering engine export
Axis is connected, and is connected between output end and rocker-arm link input terminal by bearing, and rocker-arm link output end passes through bearing and distance-variable rocker arm
Input terminal is connected；The output end of distance-variable rocker arm is fixed with moveable hinge shell.
6. a kind of all-moving wing mechanism applied to small compound helicopter as claimed in claim 5, it is characterised in that：Steering engine
Rocker arm, rocker-arm link and distance-variable rocker arm three length ratio are 30:26:45.
7. a kind of all-moving wing mechanism applied to small compound helicopter as described in claim 1, it is characterised in that：Left machine
The wing and starboard wing have angle of attack variation of the 90 degree of vertical states of vertical level to -20 degree.
8. a kind of all-moving wing mechanism applied to small compound helicopter as described in claim 1, it is characterised in that：It is fixed
Two limited blocks are designed on beam outer wall, by two limited blocks and the inter-agency cooperation of control link, limit turning for moveable hinge shell
Dynamic range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610791922.8A CN106314761B (en) | 2016-08-31 | 2016-08-31 | A kind of all-moving wing mechanism applied to small compound helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610791922.8A CN106314761B (en) | 2016-08-31 | 2016-08-31 | A kind of all-moving wing mechanism applied to small compound helicopter |
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| Publication Number | Publication Date |
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| CN106314761A CN106314761A (en) | 2017-01-11 |
| CN106314761B true CN106314761B (en) | 2018-11-23 |
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| CN201610791922.8A Active CN106314761B (en) | 2016-08-31 | 2016-08-31 | A kind of all-moving wing mechanism applied to small compound helicopter |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102022000073A1 (en) | 2022-01-12 | 2023-07-13 | Gerd BERCHTOLD | Adjustable auxiliary wing as lift support for vertical take-off aircraft with non-pivotable lift rotors |
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| CN109353505A (en) * | 2018-09-21 | 2019-02-19 | 清华大学 | A kind of tailstock formula unmanned plane of aerodynamic force/thrust vectoring complex controll |
| CN109466762A (en) * | 2019-01-08 | 2019-03-15 | 贵州剑河中和时代科技有限公司 | A kind of unmanned plane |
| CN110104177B (en) * | 2019-04-24 | 2021-01-26 | 北京航空航天大学 | Full-motion control surface for flapping rotor aircraft |
| CN110143274B (en) * | 2019-05-13 | 2021-01-15 | 中国人民解放军国防科技大学 | Wing assembly, unmanned aerial vehicle and control method of wing assembly |
| CN110979638B (en) * | 2019-12-04 | 2023-06-02 | 江西洪都航空工业集团有限责任公司 | Fixed shaft type full-moving control surface mounting structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB570455A (en) * | 1943-09-02 | 1945-07-09 | Cameron Peter | An improved aircraft |
| US2580312A (en) * | 1947-01-20 | 1951-12-25 | Hamilton K Moore | Convertible airplane and helicopter |
| GB1394177A (en) * | 1971-08-11 | 1975-05-14 | Westland Aircraft Ltd | Helicopters |
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN201737157U (en) * | 2010-07-23 | 2011-02-09 | 赵立新 | Mini-type aircraft with two parallel rotary wings |
| CN102632991A (en) * | 2012-03-27 | 2012-08-15 | 南京航空航天大学 | Wing full-motion airplane without rudder surface |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8403255B2 (en) * | 2009-08-14 | 2013-03-26 | Frederick W. Piasecki | Compound aircraft with autorotation |
-
2016
- 2016-08-31 CN CN201610791922.8A patent/CN106314761B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB570455A (en) * | 1943-09-02 | 1945-07-09 | Cameron Peter | An improved aircraft |
| US2580312A (en) * | 1947-01-20 | 1951-12-25 | Hamilton K Moore | Convertible airplane and helicopter |
| GB1394177A (en) * | 1971-08-11 | 1975-05-14 | Westland Aircraft Ltd | Helicopters |
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN201737157U (en) * | 2010-07-23 | 2011-02-09 | 赵立新 | Mini-type aircraft with two parallel rotary wings |
| CN102632991A (en) * | 2012-03-27 | 2012-08-15 | 南京航空航天大学 | Wing full-motion airplane without rudder surface |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102022000073A1 (en) | 2022-01-12 | 2023-07-13 | Gerd BERCHTOLD | Adjustable auxiliary wing as lift support for vertical take-off aircraft with non-pivotable lift rotors |
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| CN106314761A (en) | 2017-01-11 |
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