CN207029549U - A kind of hybrid tilting rotor wing unmanned aerial vehicle - Google Patents
A kind of hybrid tilting rotor wing unmanned aerial vehicle Download PDFInfo
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- CN207029549U CN207029549U CN201720289601.8U CN201720289601U CN207029549U CN 207029549 U CN207029549 U CN 207029549U CN 201720289601 U CN201720289601 U CN 201720289601U CN 207029549 U CN207029549 U CN 207029549U
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- propeller
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- cycloidal
- tilting rotor
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Abstract
The utility model is a kind of hybrid tilting rotor wing unmanned aerial vehicle, and it is mainly characterized by providing power using cycloid propeller and propeller combination.The cycloidal paddle propeller that two propeller piggyback pods and afterbody are slightly located in power section by the wing wing is formed, two propeller piggyback pods can carry out wide-angle and vert, realize the transformation of thrust direction, cycloidal paddle propeller is by cycloidal oar blade, support, adjusting rod, cycloid propeller rotating shaft, drive device, Eccentric Circular Ring and Eccentric Circular Ring controller are formed, and change the direction of afterbody thrust by the variation to Eccentric Circular Ring position., can be with VTOL and hovering when unmanned plane is in more gyroplane states；When unmanned plane is in fixed-wing aircraft state, flying speed is very fast, and efficiency is higher.The utility model has merged the advantages of more rotors and fixed-wing, has broad application prospects.
Description
Technical field
The utility model belongs to aviation aircraft design field, and in particular to one kind is mixed using cycloid propeller with propeller
The tilting rotor wing unmanned aerial vehicle of conjunction.
Background technology
For a long time, people are seeking to have the aircraft of more gyroplane and fixed-wing aircraft advantages concurrently always.By visiting for many years
Rope and practice, the V-22 " osprey " for such as U.S.'s first generation tilting rotor prototype verification machine XV-15 occur, being on active service vert
Gyroplane, " hawkeye " tilting rotor wing unmanned aerial vehicle etc., important function has been played in dual-use field, before having wide development
Scape.Tilting rotor wing unmanned aerial vehicle not only has the advantages that multi-rotor unmanned aerial vehicle VTOL, hovering, while also has and fixation
The suitable flying speed of wing aircraft, voyage and load-carrying ability.But due to the tiltrotor that osprey is DCB Specimen, flight control system
Unite complex, hang down fly and vert hang down fly it is flat fly over the state of flight crossed when, it is poor longitudinal stability to be present, operating difficulties
The problems such as.
In addition, the research for cycloid propeller technology continue for longer time, pass through existing theory analysis and reality
Test and understand, the exhibition of cycloid propeller blade passes through the axis pivot parallel with oar disk shaft axis to the diameter parallel with oar disk rotating shaft
On oar disk, blade can be swung around pivot.Blade is as lifting surface, during oar disk axis of rotation, its angle of attack
Experience changes from zero-incidence to the maximum angle of attack, then from the maximum angle of attack to the continuous cycles of zero-incidence, this elevating movement of blade
The unsteady aerodynamic effect brought can greatly improve the pneumatic efficiency of cycloid propeller.In addition, blade is adjusted by controlling organization
Maximum angle of attack size, thus it is possible to vary the pulling force size of cycloid propeller；And orientation during by adjusting blade angle of attack maximum on oar disk
Angle, then it can produce the pulling force of the either direction in the plane of oar disk rotating shaft, control of the cycloid propeller to thrust size and Orientation
System is simple and efficient.
Utility model content
It is intended to for deficiency existing for above-mentioned osprey tiltrotor, and the characteristic that cycloid propeller has, the utility model
There is provided a kind of control simply, stability is strong, and reliability is high, new tilting rotor wing unmanned aerial vehicle easy to operation.
To realize technical purpose of the present utility model, the utility model provides following multiple technologies scheme：
A kind of hybrid tilting rotor wing unmanned aerial vehicle, including fuselage, fixed wing and fixed empennage, it is characterised in that described
Unmanned plane also include positioned at wing can tilted propeller piggyback pod and the cycloidal paddle propeller positioned at empennage.
According to the unmanned plane described in any of the above-described technical scheme, it is characterised in that it is described can tilted propeller be located at wing
Both ends.
According to the unmanned plane described in any of the above-described technical scheme, it is characterised in that positioned at the rotation side of the propeller of both wings
To opposite.
According to the unmanned plane described in any of the above-described technical scheme, it is characterised in that the fixed empennage includes horizontal component
And vertical portion, it is L-shaped per side.
According to the unmanned plane described in any of the above-described technical scheme, it is characterised in that the cycloidal paddle propeller includes cycloid
Paddle blade, cycloid propeller support, adjusting rod, cycloid propeller rotating shaft, drive device, Eccentric Circular Ring and Eccentric Circular Ring controller, the pendulum
Line oar propeller changes the direction of afterbody thrust by the Eccentric Circular Ring controller to the control of Eccentric Circular Ring position.
According to the unmanned plane described in any of the above-described technical scheme, it is characterised in that the propeller piggyback pod and the pendulum
The power type of line oar propeller can be electronic, oily dynamic or oil electricity mixing.
According to the unmanned plane described in any of the above-described technical scheme, it is characterised in that the cycloidal paddle propeller includes four
Cycloidal oar blade.
According to the unmanned plane described in any of the above-described technical scheme, it is characterised in that when aircraft is flat to fly, two of which phase
To cycloidal oar blade and aircraft fuselage axis where horizontal plane it is substantially coplanar.
In one more specifically technical scheme, the utility model provides a kind of tilting rotor using cycloid rudder flap
Unmanned plane, it is mainly characterized by providing power using cycloid propeller and propeller combination, is laid out compared to the DCB Specimen of osprey, this reality
It is made up of with Novel power system two propeller piggyback pods at wing both ends and the cycloidal paddle propeller three parts of afterbody, in etc.
Lumbar triangle shape is distributed.Two propeller piggyback pods can realize that wide-angle is verted by steering wheel and connecting rod；Cycloidal paddle propeller by
Cycloidal oar blade, support, adjusting rod, cycloid propeller rotating shaft, drive device, Eccentric Circular Ring and Eccentric Circular Ring controller are formed, and are passed through
Variation to Eccentric Circular Ring position changes the direction of afterbody thrust, realizes full vector thrust, and responds very fast.Three power ends
The transformation of thrust direction can allow unmanned plane to realize the conversions of more rotor and fixed-wing both of which；When wing both ends, propeller moves
Power cabin is verted upwards, and when cycloidal paddle propeller thrust is downward, unmanned plane is in more gyroplane patterns, can be with VTOL and aerial
Hovering；When wing both ends, propeller piggyback pod is verted backward, and cycloid propeller thrust is closed, 4 cycloid propeller blades and the flat winged side of aircraft
To parallel, unmanned plane is in fixed-wing pattern.
In one more specifically technical scheme, the utility model uses power of the cycloidal paddle propeller as afterbody
End, cycloid propeller rotating shaft is fixed on fuselage, and support is formed by four around the uniform extension bar of cycloid propeller rotating shaft, and can be around
Cycloid propeller rotating shaft rotation；Cycloid propeller is made up of the blade of 4 symmetrical airfoils, and their leading edge is outer with 4 extension bars respectively
End is be hinged；Adjusting rod is 4, and respectively with being hinged at cycloidal oar blade trailing edge, the other end can be in Eccentric Circular Ring for their one end
Upper slip；Eccentric Circular Ring has two frees degree, can be in the plane translational motion parallel to the aircraft plane of symmetry, Eccentric Circular Ring control
Device processed is fixed on fuselage, controls the motion of Eccentric Circular Ring.
The beneficial effects of the utility model include following any one：
The utility model is a kind of new verting by three power ends (each one of wing both ends, empennage one) composition
Gyroplane, have more rotor and fixed-wing both of which concurrently.VTOL and hovering can be carried out under more rotor modes,
It is taken off landing without runway or other devices, the flight operation of high speed can be carried out under fixed-wing pattern, fly
Efficiency is higher.Three power ends have more a cycloid propeller in afterbody compared to the tiltrotor (such as osprey) of two power ends and promoted
Device, when hanging down winged, aircraft adds the torque that pitching can be controlled to operate, and this make it that aircraft is longitudinally simpler in operation
Single, stability is stronger, and reliability is higher.
Power end of the cycloidal paddle propeller as afterbody, has compared to airscrew thrust device or ducted fan device
Very big advantage：First, cycloid propeller is simple in construction, and weight is small, and eliminates heavy inclining rotary mechanism, substantially reduces aircraft
Weight, be advantageous to the lifting of aircraft range and the raising of mobility；Secondly, cycloidal paddle propeller by control the angle of attack of blade come
Control the size and Orientation of thrust, and the size and Orientation of thrust can transient change, control is simple and efficiently, as afterbody
Power end, be advantageous to improve aircraft hang down fly when stability and mobility；Moreover, no matter cycloid propeller is with more powerful rotations,
Noise is all very low；Finally, as the power end of afterbody, when aircraft hangs down winged, cycloid propeller will not produce extra yawing.
When aircraft is flat to fly, cycloid propeller support and cycloidal oar blade are fixed on ad-hoc location, relative two on support
The face of horizontal plane three where plane and fuselage axis where blade is coplanar, and two other relative blade plane is parallel to upper
The coplanar plane in three faces is stated, now, airplane tail group front face area reaches minimum, and when putting down winged, caused resistance is smaller.Moreover, with
That coplanar two panels blade of horizontal plane where fuselage axis can as aircraft is flat fly when horizontal stabilizer, two other blade
It can be rotated along the pin joint of edge and support, can be as the elevator put down when flying.
Brief description of the drawings
Fig. 1 is the flat winged state overall pattern of the hybrid tilting rotor wing unmanned aerial vehicle of the utility model；
Fig. 2 is the vertical winged state overall pattern of the hybrid tilting rotor wing unmanned aerial vehicle of the utility model；
Fig. 3 is the hybrid tilting rotor wing unmanned aerial vehicle cycloidal paddle propeller detail view of the utility model；
Fig. 4 is afterbody detail view when the hybrid tilting rotor wing unmanned aerial vehicle of the utility model is flat winged；
1 empennage rudder face in figure, 2 empennages, 3 cycloidal paddle propellers, 4 wings, 5 fuselages, 6 ailerons, 7 propellers, 8 propellers move
Power cabin, 9 cycloid propeller rotating shafts, 10 Eccentric Circular Rings, 11 drive devices, 12 cycloidal oar blades, 13 adjusting rods, 14 supports, 15 off-centre operations
Ring controller
Embodiment
In order that technical problem, technical scheme and beneficial effect that the utility model solves are more clearly understood, below
With reference to drawings and Examples, the utility model is further elaborated.It should be appreciated that specific implementation described herein
Example only to explain the utility model, is not used to limit the utility model.
In a specific embodiment, propeller piggyback pod 8 can rotate around the shaft, and cycloidal paddle propeller 3 can appoint
Meaning with promptly changing in aircraft plane of symmetry thrust size and Orientation, realize cutting between more rotor mode and fixed-wing patterns
Change.
When unmanned plane is in more rotor modes, propeller piggyback pod 8 verts to, cycloid propeller vertical with the axis of fuselage 5 upwards
Propeller 3 changes the position of Eccentric Circular Ring by Eccentric Circular Ring controller, to adjust the direction of thrust caused by cycloid propeller and big
It is small, make caused thrust downward, be of moderate size, and by the stability for flying control holding aircraft.During aircraft forward-reverse, propeller
Piggyback pod 8 and the Differential Control of cycloidal paddle propeller 3；When aircraft side flies, the Differential Control of left-and-right spiral oar piggyback pod 8；Yawed flight
When, it is controlled by the tilt angle of the first two propeller piggyback pods 8 of wing or so steering wheel adjustment end.Therefore, unmanned plane exists
Hang down when flying, can realize VTOL, hovering, it is preceding fly, it is rear fly, the action such as side flies.
When unmanned plane is in fixed-wing pattern, propeller piggyback pod 8 tilts forward, cycloid propeller support and cycloidal oar blade
It is fixed on ad-hoc location, the plane on support where two relative blades and the face of horizontal plane three where fuselage axis are total to
Face, two other relative blade plane is parallel to the coplanar plane in above-mentioned three face, and now, airplane tail group front face area reaches most
Small, when putting down winged, caused resistance is smaller.Fly moreover, that two panels blade coplanar with the horizontal plane where fuselage axis can be used as
Horizontal stabilizer when machine is flat winged, two other blade can rotate along the pin joint of edge and support, can be used as flat fly
When elevator.Rolling movement is controlled by aileron rudder face 6, and pitching and driftage operation are carried out by empennage rudder face 1, and operation format is general
Logical fixed wing aircraft is consistent.In fixed-wing mode flight, the speed of aircraft horizontal movement, high-speed maneuver is realized.
Claims (8)
1. a kind of hybrid tilting rotor wing unmanned aerial vehicle, including fuselage, fixed wing and fixed empennage, it is characterised in that the nothing
It is man-machine also include positioned at wing can tilted propeller piggyback pod and the cycloidal paddle propeller positioned at empennage.
2. hybrid tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that it is described can tilted propeller power
Freight space is in the both ends of wing.
3. hybrid tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that positioned at the rotation of both wings propeller
In the opposite direction.
4. hybrid tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that the fixed empennage includes level
Part and vertical portion.
5. hybrid tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that the cycloidal paddle propeller includes
Cycloidal oar blade, cycloid propeller support, adjusting rod, cycloid propeller rotating shaft, drive device, Eccentric Circular Ring and Eccentric Circular Ring controller, institute
State cycloidal paddle propeller and the direction of afterbody thrust is changed to the control of Eccentric Circular Ring position by the Eccentric Circular Ring controller.
6. hybrid tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that the propeller piggyback pod and institute
The power type for stating cycloidal paddle propeller can be electronic, oily dynamic or oil electricity mixing.
7. hybrid tilting rotor wing unmanned aerial vehicle according to claim 5, it is characterised in that the cycloidal paddle propeller includes
Four cycloidal oar blades.
8. hybrid tilting rotor wing unmanned aerial vehicle according to claim 7, it is characterised in that when aircraft is flat to fly, wherein
Horizontal plane where two relative cycloidal oar blades and aircraft fuselage axis is substantially coplanar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720289601.8U CN207029549U (en) | 2017-03-23 | 2017-03-23 | A kind of hybrid tilting rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720289601.8U CN207029549U (en) | 2017-03-23 | 2017-03-23 | A kind of hybrid tilting rotor wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN207029549U true CN207029549U (en) | 2018-02-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720289601.8U Active CN207029549U (en) | 2017-03-23 | 2017-03-23 | A kind of hybrid tilting rotor wing unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533319A (en) * | 2018-12-07 | 2019-03-29 | 湖北航天飞行器研究所 | A kind of tilting rotor unmanned vehicle structural system with the overlap joint wing |
| WO2022067492A1 (en) * | 2020-09-29 | 2022-04-07 | 瑞鉴航太科技股份有限公司 | Aerial vehicle |
-
2017
- 2017-03-23 CN CN201720289601.8U patent/CN207029549U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533319A (en) * | 2018-12-07 | 2019-03-29 | 湖北航天飞行器研究所 | A kind of tilting rotor unmanned vehicle structural system with the overlap joint wing |
| WO2022067492A1 (en) * | 2020-09-29 | 2022-04-07 | 瑞鉴航太科技股份有限公司 | Aerial vehicle |
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