CN106314761A - All-moving wing mechanism applied to small compound helicopter - Google Patents
All-moving wing mechanism applied to small compound helicopter Download PDFInfo
- Publication number
- CN106314761A CN106314761A CN201610791922.8A CN201610791922A CN106314761A CN 106314761 A CN106314761 A CN 106314761A CN 201610791922 A CN201610791922 A CN 201610791922A CN 106314761 A CN106314761 A CN 106314761A
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- Prior art keywords
- wing
- small compound
- moving
- helicopter
- compound helicopter
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Classifications
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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 invention provides an all-moving wing mechanism applied to a small compound helicopter. The mechanism comprises a left wing and a right wing and is characterized by further comprising wing main beams, two movable hinges, a fixing beam and operating link mechanisms, wherein the left wing and the right wing are symmetrically arranged on two sides of a helicopter body, and the wing main beam arranged in the expansion direction is mounted in each wing; a variable pitch shaft is sleeved with a movable hinge casing internally and externally through bearings to constitute each movable hinge, and a rotating pair is formed; the two movable hinges are used for realizing connection between each of the left wing and the right wing and the end part of the fixing beam; the middle section of the fixing beam is mounted on a support in the helicopter body; each movable hinge is controlled by one corresponding operating link mechanism, rotation of the movable hinge casings relative to the variable pitch shafts is realized, and accordingly, the left wing and the right wing rotate around axes of the corresponding wing main beams, and attack angles of the left wing and the right wing are changed. The all-moving wing mechanism has the advantage that the problems of hover performance reduction and interference resistance increase which are caused by wing components of the small compound helicopters are solved.
Description
Technical field
The invention belongs to technical field of aerospace, particularly relate to a kind of all-moving wing being applied to small compound helicopter
Mechanism.
Background technology
Composite helicopter is for pursuing speed and to give birth to.Say in general sense composite helicopter be by fixed-wing parts 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
Rise machine layout comprise composite wing system (sharing rotor lift) and be installed on the propulsion system of afterbody (advance providing extra pushes away
Power)；
Composite helicopter has many advantages, first its speed to breach the limit of pure helicopter, due to its rotor
Unloaded, helicopter vibration level is relatively low, owing to wherein high speed pneumatic efficiency is high, when adding voyage and boat, and because it increases
Lift thrust aid system, the mobility of aircraft also promotes.But composite helicopter also has some shortcomings, owing to it increases
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 adds helicopter and enters the difficulty of spin states, makes the autorotative glide ability of aircraft decline, and safety damages.
For composite helicopter, wing had both been to provide the vitals of lift unloading rotor, was again that hovering is with front
Main interference source when flying.This aerodynamic loss is especially obvious hovering when, because of the power that flies before not having during hovering, wing without
Pneumatic effect, keeps flat close to flat board effect, stops purling, be huge sources of resistance, reduce hovering efficiency, affect combined type straight
The machine of the liter performance when hovering.Existing composite helicopter speed eagle selects 90 degree of the aileron bottom when hovering, reduces hovering
Loss, and aileron area is very big, reduces the wing drawback when hovering as far as possible.But the most still there is lost area.If adopting
With complete dynamic aerofoil, this has complete dynamic realization in fixed-wing horizontal tail, reduces by a rudder face and do the motion of full empennage, it is provided that the inclined moment of rudder.
Fixed wing airplane airfoil member have no complete dynamic application to remove aileron structure, the weight issue brought due to its structural strength is not
Calculate.Before when flying helicopter break down, spin situation need to be entered, wing is again one and hinders parts, and rotor will be hindered to enter
Autorotation.Flying transition stage before composite helicopter hovering turns, fuselage attitude angle changes, and makes the fixed wing angle of attack be in
Nonideality, performance is the best.
Summary of the invention
In order to overcome above-mentioned the deficiencies in the prior art, the present invention provides a kind of and is applied to the complete dynamic of small compound helicopter
Wing structure, to solve the problem that small compound helicopter airfoil member reduces hovering performance, increases interference drag.Full motivation
The wing casts out aileron parts, can change the wing angle of attack for different flight state, make wing be at optimum under each mission phase
Angle of attack position, provides rudder face operating torque simultaneously, alleviates rotor control burden, and in specific fault, (engine cut-off, rotor is unpowered
Rotate) in the case of reduce wing harmful effect that rotor is become a mandarin.
The present invention is applied to the all-moving wing mechanism of small compound helicopter, and one is applied to small compound helicopter
All-moving wing mechanism, including port wing, starboard wing, wing girder, moveable hinge, fixing beam and control link mechanism.
Described port wing and starboard wing are symmetricly set in fuselage both sides, and inside is mounted on along exhibition to the wing master arranged
Beam.Moveable hinge is two, is consisted of bearing internal external socket with moveable hinge shell pitch change axes, forms revolute pair.
Above-mentioned two moveable hinge is respectively intended to realize the connection between port wing, starboard wing and fixing beam between end；Fixing beam
Stage casing is installed on fuselage interior support.Two moveable hinges are respectively by a set of control link mechanism controls, it is achieved moveable hinge shell
Rotating relative to pitch change axes, and then make port wing and starboard wing around the rotation of wing girder axis, it is achieved port wing and starboard wing
The angle of attack change.
It is an advantage of the current invention that:
1, the present invention is applied to the all-moving wing mechanism of small compound helicopter, solves composite helicopter multiplexing
During condition flight, the wing angle of attack fixes the harmful effect brought；
2, the present invention is applied to the all-moving wing mechanism of small compound helicopter, simple in construction, can be applicable to small-sized (total
Weight about below 200kg) composite helicopter；
3, the present invention is applied to the all-moving wing mechanism of small compound helicopter, the wing when composite helicopter hovers
Vertically, reduce the harmful effect to hovering efficiency, improve full machine pneumatic efficiency；Fly over before composite helicopter hovering turns and tide over
Cheng Zhong, the not random body attitude angle of the all-moving wing angle of attack changes, and can preferably adapt to transient process, accelerate transitioning processes, reduce
Power attenuation, improves final flight speed；When flying before composite helicopter is stable, all-moving wing mechanism operating airfoil water
Flat, finely tune the angle of attack, and the differential control angle of attack according to air-flow, it is possible to provide with the rolling moment of fixed-wing wing aileron equivalence；?
When composite helicopter is eager to slow down, wing can tune to vertical position and provides flaps effect, when there is accident in helicopter,
Rotatable the getting out of the way of wing becomes a mandarin, and reduction wing obstruction rotor becomes a mandarin and enters the difficulty of spin.
Accompanying drawing explanation
Fig. 1 is all-moving wing mechanism structure schematic diagram of the present invention；
Fig. 2 is moveable hinge and connected mode schematic diagram thereof in all-moving wing mechanism of the present invention；
When Fig. 3 is to fly before helicopter in all-moving wing mechanism of the present invention, control link structural scheme of mechanism；
When Fig. 4 is helicopter hovering in all-moving wing mechanism of the present invention, control link structural scheme of mechanism；
Fig. 5 is the all-moving wing mechanism of the present invention view when flying before helicopter；
Fig. 6 is the all-moving wing mechanism of the present invention view when helicopter hovers.
In figure:
1-port wing 2-starboard wing 3-wing girder
4-moveable hinge 5-fixes beam 6-control link mechanism
7-fuselage 8-limited block 401-moveable hinge shell
402-bearing sleeve 403-pitch change axes 404-front portion rolling bearing
405-rear portion rolling bearing 406-top cover 601-steering wheel
602-steering wheel rocking arm 603-rocker-arm link 604-distance-variable rocker arm
Detailed description of the invention
The present invention is further described with embodiment below in conjunction with the accompanying drawings.
All-moving wing mechanism of the present invention includes the composite helicopter being applied to, wing and the company thereof to composite helicopter
The mode of connecing improves, including port wing 1, starboard wing 2, wing girder 3, moveable hinge 4, fixing beam 5 and control link mechanism 6,
As shown in Figure 1.
Described port wing 1 is symmetricly set in fuselage 7 left and right sides with starboard wing 2, and inside is mounted on along exhibition to setting
Wing girder 3；In conjunction with considering of aerodynamic moment and structural strength, in the present invention chordwise location of wing girder 3 be positioned at away from
The position of wing chord length leading edge 30% chord length length, and between wing aerodynamic focus and maximum gauge.Port wing 1 and right machine
Wing girder 3 end on the wing 2 uses same way to be provided with moveable hinge 4, and by moveable hinge 4 respectively with fixing beam 5 two ends
It is connected.
Described moveable hinge 4 includes moveable hinge shell 401, bearing sleeve 402 and pitch change axes 403, as shown in Figure 2；Wherein, live
Dynamic hinge shell 401 forward end is designed with cylindric connection end, inserts in the slot of wing girder 3 end coaxial design, passes through
Glued joint fixing.Pitch change axes 403 is coaxially disposed with moveable hinge shell 401, and front portion is positioned at moveable hinge shell 401, passes through moveable hinge
Two rolling bearings axially arranged in shell 401 are connected with moveable hinge shell 401, can realize the smooth of moveable hinge shell 401
Roll.Pitch change axes 403 end inserts in the cylinder-like structure of fixing beam 5 end design, runs through bolt by sidewall and realizes displacement
Axle 403 is fixed with fixing beam 5.Above-mentioned two rolling bearing is made to be respectively anterior rolling bearing 404 and end rolling bearing 405,
Then anterior rolling bearing 404 with the mounting means of rear portion rolling bearing 405 is: moveable hinge is passed through in anterior rolling bearing 404 outer ring
The locating shoulder of shell 401 inwall design, it is achieved forward location；Moveable hinge casing ends is passed through in end rolling bearing 405 outer ring
On annular gasket, it is achieved backward location；Relative between anterior rolling bearing 404 outer ring and end housing washer 405
Location, is realized by the bearing sleeve 402 being enclosed within pitch change axes 403.Anterior rolling bearing 404 inner ring is by coaxially solid by bolt
It is scheduled on the top cover 406 on pitch change axes 403 front end face, it is achieved forward location；Anterior rolling bearing 404 inner ring and end rolling bearing
Relative localization between 405 inner rings, is realized by the annular boss of the upper design of pitch change axes 403 circumference；This annular boss is also simultaneously
Achieve the forward location of end rolling bearing 405 inner ring；The backward location of end rolling bearing 405 inner ring, by fixing beam 5
The annular end face of end realizes.From there through the rolling of these two moveable hinge shells 401 of control, port wing 1 can be realized with right
The angle of attack of wing 2 changes, and port wing 1 and the discriminable flexible change angle of attack of starboard wing 2, it is achieved 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 fixing beam 5, is bolted the mounting bracket being installed within fuselage 7
On, and it is provided with yielding rubber pad between fixing beam 5 and mounting bracket；Realize between all-moving wing of the present invention and fuselage 7 with this
Install fixing.Above-mentioned all-moving wing is installed on fuselage 7 upper position, reduces rotor and disturbs with wing aerodynamic；All-moving wing simultaneously
And also need between fuselage 7 to meet: the pneumatic focus of all-moving wing and fuselage 7 center of gravity are respectively positioned on rotor shaft front, near rotor shaft, and
It is positioned at same to be perpendicular on the straight line of horizontal plane.
Above-mentioned port wing 1 and the control becoming the angle of attack of starboard wing 2, realized by a set of control link mechanism 6 respectively.Handle
Linkage 6 includes steering wheel 601, steering wheel rocking arm 602, rocker-arm link 603 and distance-variable rocker arm 604, as shown in Figure 3, Figure 4.Wherein,
The input of steering wheel rocking arm 602 and steering wheel 601 output shaft fixed connection, pass through Minisize axial between outfan and rocker-arm link 603 input
Holding connected, rocker-arm link 603 outfan is connected with distance-variable rocker arm 604 input by miniature bearing；The output of distance-variable rocker arm 604
End is fixed with moveable hinge shell 401；And then can be by steering wheel rocking arm 602, rocker-arm link 603, distance-variable rocker arm 604 and steering wheel rocking arm
A quadric chain it is considered as between the pivot center line of 602 inputs and distance-variable rocker arm 604 outfan；Wherein steering wheel shakes
Arm 602, rocker-arm link 603 and distance-variable rocker arm 604 three's length are than for 30:26:45.Thus port wing 1 and starboard wing 2 are by behaviour
It is vertical with 90 degree of starboard wing 2 that angle change in 120 degree of steering wheel 601 output shaft can be converted to port wing 1 by vertical connecting rod mechanism
State is to the angle of attack variation of-20 degree, as shown in Figure 5, Figure 6；And by designing two limited blocks on fixing beam 5 outer wall, limit
The slewing area of distance-variable rocker arm 604, and then limit port wing 1 with starboard wing 2 angle of attack variation beyond steering range, i.e.-20 degree
To 90 degree, it is to avoid aerodynamic force burst effect causes the wing angle of attack to outrange the excursion injury to control link mechanism.
Apply the composite helicopter of all-moving wing mechanism of the present invention when being in floating state, for the reduction of maximum possible
Interference, controls port wing 1 by control link mechanism 6 and is in 90 degree of vertical states, as shown in Figure 5 with starboard wing 2；By behaviour
Vertical connecting rod mechanism 6 controls wing and answers air velocity to change, and is gradually deflected to level, makes composite helicopter by floating state
Flying state before transitting to stablize, now port wing 1 and starboard wing 2 are in level, and the angle of attack can with positive and negative 20 degree becomes
Change scope, as shown in Figure 6, thus can allow port wing 1 and starboard wing 2 avoid the harmful effect of fuselage 7 attitude angle change, and pass through
Differential control can provide the operating torque being equivalent to aileron rolling.When composite helicopter is eager to slow down, wing can tune to
Vertical position state, it is possible to provide should the flap effect of flight demand.When accident occurs in composite helicopter, by the company of 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 to starboard wing 2
Enter the difficulty of spin.
Claims (9)
1. it is applied to an all-moving wing mechanism for small compound helicopter, including port wing and starboard wing；It is characterized in that:
Also include wing girder, moveable hinge, fixing beam and control link mechanism；
Described port wing and starboard wing are symmetricly set in fuselage both sides, and inside is mounted on along exhibition to the wing girder arranged；Live
Dynamic hinge is two, is consisted of bearing internal external socket with moveable hinge shell pitch change axes, forms revolute pair；
Above-mentioned two moveable hinge is respectively intended to realize the connection between port wing, starboard wing and fixing beam between end；Fixing beam stage casing
It is installed on fuselage interior support；Two moveable hinges are respectively by a set of control link mechanism controls, it is achieved moveable hinge shell is relative
The rotation of pitch change axes, and then make port wing and starboard wing around the rotation of wing girder axis, it is achieved port wing is attacked with starboard wing
Angle changes.
A kind of all-moving wing mechanism being applied to small compound helicopter, it is characterised in that: wing
The chordwise location of girder is positioned at the position away from wing chord length leading edge 30% chord length length, and thick between wing aerodynamic focus and maximum
Between degree.
A kind of all-moving wing mechanism being applied to small compound helicopter, it is characterised in that: fixing
Yielding rubber pad it is provided with between beam and mounting bracket.
A kind of all-moving wing mechanism being applied to small compound helicopter, it is characterised in that: install
In fuselage upper position；Need to meet: the pneumatic focus of all-moving wing and body nodal point are respectively positioned on rotor shaft front, near rotation simultaneously
Wing axle, and be positioned at same and be perpendicular on the straight line of horizontal plane.
A kind of all-moving wing mechanism being applied to small compound helicopter, it is characterised in that: movable
Hinge case nose end is designed with cylindric connection end, and the slot inserting wing girder end is fixed；Pitch change axes end inserts solid
Fix after determining beam end.
A kind of all-moving wing mechanism being applied to small compound helicopter, it is characterised in that: handle
Linkage includes steering wheel, steering wheel rocking arm, rocker-arm link and distance-variable rocker arm；Wherein, the input of steering wheel rocking arm exports with steering wheel
Axle is connected, and is connected by bearing between outfan with rocker-arm link input, and rocker-arm link outfan passes through bearing and distance-variable rocker arm
Input is connected；The outfan of distance-variable rocker arm is fixed with moveable hinge shell.
A kind of all-moving wing mechanism being applied to small compound helicopter, it is characterised in that: steering wheel
Rocking arm, rocker-arm link and distance-variable rocker arm three's length are than for 30:26:45.
A kind of all-moving wing mechanism being applied to small compound helicopter, it is characterised in that: left machine
The wing and starboard wing have 90 degree of vertical states angle of attack variation to-20 degree of vertical level.
A kind of all-moving wing mechanism being applied to small compound helicopter, it is characterised in that: fixing
Design two limited blocks on beam outer wall, coordinate by two limited blocks are inter-agency with control link, restraint hinge shell turn
Dynamic scope.
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106314761A true CN106314761A (en) | 2017-01-11 |
| CN106314761B 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 (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106890456A (en) * | 2017-02-13 | 2017-06-27 | 深圳市龙云创新航空科技有限公司 | A kind of modular event driven component and built-up pattern |
| CN109094767A (en) * | 2018-09-07 | 2018-12-28 | 佛山皖和新能源科技有限公司 | A kind of fixed-wing unmanned plane quick-replaceable wing |
| 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 |
| CN110104177A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | It is a kind of for flutterring all movable rudder face of rotor craft |
| CN110143274A (en) * | 2019-05-13 | 2019-08-20 | 中国人民解放军国防科技大学 | Wing assembly, unmanned aerial vehicle and control method of wing assembly |
| CN110418755A (en) * | 2017-11-28 | 2019-11-05 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle |
| CN110979638A (en) * | 2019-12-04 | 2020-04-10 | 江西洪都航空工业集团有限责任公司 | Dead axle type full-motion control surface mounting structure |
| CN111479751A (en) * | 2017-07-21 | 2020-07-31 | Av8Or Ip有限公司 | Hybrid multi-rotor unmanned aerial vehicle with adjustable wings |
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| 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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| GB570455A (en) * | 1943-09-02 | 1945-07-09 | Cameron Peter | An improved aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106890456A (en) * | 2017-02-13 | 2017-06-27 | 深圳市龙云创新航空科技有限公司 | A kind of modular event driven component and built-up pattern |
| CN111479751A (en) * | 2017-07-21 | 2020-07-31 | Av8Or Ip有限公司 | Hybrid multi-rotor unmanned aerial vehicle with adjustable wings |
| CN111479751B (en) * | 2017-07-21 | 2023-10-27 | Av8Or Ip有限公司 | Hybrid multi-rotor unmanned aerial vehicle with adjustable wings |
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| CN109094767A (en) * | 2018-09-07 | 2018-12-28 | 佛山皖和新能源科技有限公司 | A kind of fixed-wing unmanned plane quick-replaceable wing |
| 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 |
| CN110104177A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | It is a kind of for flutterring all movable rudder face of rotor craft |
| CN110104177B (en) * | 2019-04-24 | 2021-01-26 | 北京航空航天大学 | Full-motion control surface for flapping rotor aircraft |
| CN110143274A (en) * | 2019-05-13 | 2019-08-20 | 中国人民解放军国防科技大学 | Wing assembly, unmanned aerial vehicle and control method of wing assembly |
| CN110979638A (en) * | 2019-12-04 | 2020-04-10 | 江西洪都航空工业集团有限责任公司 | Dead axle type full-motion control surface mounting structure |
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| CN106314761B (en) | 2018-11-23 |
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