CN112009674A - Tilt wing mechanism and have unmanned aerial vehicle of tilt wing mechanism - Google Patents
Tilt wing mechanism and have unmanned aerial vehicle of tilt wing mechanism Download PDFInfo
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- CN112009674A CN112009674A CN202010923570.3A CN202010923570A CN112009674A CN 112009674 A CN112009674 A CN 112009674A CN 202010923570 A CN202010923570 A CN 202010923570A CN 112009674 A CN112009674 A CN 112009674A
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- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention belongs to the technical field of unmanned aerial vehicles, and discloses a tilt wing mechanism, which comprises a fixed wing and rotary wings arranged at two ends of the fixed wing respectively, wherein each rotary wing comprises: the tilting wing mechanism comprises a first wing and a second wing, wherein the fixed wing is connected with the first wing in a rotating mode, the fixed wing is connected with the second wing in a rotating mode, the tilting wing mechanism further comprises a drive, the rotating wing is opposite to the rotating power unit of the fixed wing, a first motor is arranged on the first wing, and a second motor is arranged on the second wing. The invention also discloses an unmanned aerial vehicle with the tilt wing mechanism, which comprises the tilt wing mechanism, a fuselage and an empennage unit, wherein the worm wheel and the rotating motor are arranged in the fuselage. Compared with the prior art, the unmanned aerial vehicle with the tilt wing mechanism has the advantages of good reliability, long service life of the steering engine, high wind resistance and high flight quality.
Description
[ technical field ] A method for producing a semiconductor device
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a tilt wing mechanism and an unmanned aerial vehicle with the tilt wing mechanism.
[ background of the invention ]
The Unmanned Aerial Vehicle (UAV) has the advantages of high flexibility, light weight, controllability and the like, so that the UAV is widely applied, and in the field of environmental protection, the unmanned aerial vehicle remote sensing technology is utilized to perform environmental evaluation, acceptance inspection and water and soil monitoring on construction projects to complete an environmental protection management task; and completing environment monitoring tasks from land vegetation change, water pollution estimation, habitat statistics and the like. In the aspect of resource management, the unmanned aerial vehicle image equipment is mainly used for completing tasks such as land resource and geographic information parameter statistics. In agricultural production, the unmanned aerial vehicle carrying device is used for completing the tasks of crop yield estimation, pest and disease monitoring, field management and the like. In the aspect of post-disaster rescue, the data statistics of natural disasters, real-time monitoring of disaster areas, search and rescue in disasters, post-disaster situation assessment and the like are completed. Unmanned aerial vehicle also gets on the stage gradually in the aspect of express delivery transportation, circuit are patrolled and examined etc..
And the use of VTOL technique adds up for unmanned aerial vehicle's development is good, the outstanding performance of zero distance take off and land, stable flight makes VTOL unmanned aerial vehicle become the mainstream of unmanned aerial vehicle design down when adding fixed wing long endurance. The VTOL fixed wing UAVs are divided into a plurality of types, namely tilting type (rotor wings or wings) VTOL UAVs, combined type VTOL UAVs, tailstock type VTOL UAVs and ducted fan VTOL UAVs. Compared with a helicopter, the vertical take-off and landing unmanned aerial vehicle has the advantages that the design cost is greatly reduced, the controllability and the stability of the unmanned aerial vehicle are higher on the basis of a given task, and the endurance time is longer. Compared with a gyroplane, the gyroplane is certainly not as much as a vertical take-off and landing unmanned aerial vehicle in the aspect of endurance; secondly, the rotorcraft has poor wind resistance and low flying speed. Gyroplanes are often not used when large mission flights are required. Compared with a common fixed wing, the vertical take-off and landing unmanned aerial vehicle has more excellent performance in areas such as a forest farm and a mountain land with poor take-off and landing environment. Unmanned aerial vehicle's among the correlation technique tilting rotor adopts the mode of rotating electrical machines mostly, and the motor is when tilting process and locking, and the steering wheel is in the stress state always, need bear locking moment. The moment is directly used on the rotating shaft of the steering engine, so that the bearing capacity and the service life of the steering engine gear set are reduced, and the flight reliability of the unmanned aerial vehicle is greatly reduced.
Therefore, it is necessary to provide a new tilt wing mechanism and an unmanned aerial vehicle having the same to solve the above technical problems.
[ summary of the invention ]
The technical problems to be solved by the invention are as follows: the utility model provides a wing mechanism and an unmanned aerial vehicle that has this wing mechanism that verts, its good reliability, flight quality height vert.
In order to achieve the above technical effects, the present invention provides a tilt wing mechanism, including a fixed wing and a rotary wing respectively disposed at two ends of the fixed wing, wherein the rotary wing includes: the tilting wing mechanism comprises a first wing and a second wing, wherein the fixed wing is connected with the first wing in a rotating mode, the fixed wing is connected with the second wing in a rotating mode, the tilting wing mechanism further comprises a drive, the rotating wing is opposite to the rotating power unit of the fixed wing, a first motor is arranged on the first wing, and a second motor is arranged on the second wing.
Preferably, the rotary power unit includes: worm wheel, worm, rotating electrical machines, the worm wheel is located the stationary vane below, the worm is followed the length direction of stationary vane runs through the stationary vane just the both ends of worm extend to respectively in first wing and the second wing, the worm with the stationary vane rotates and links to each other, the worm with first wing is fixed continuous, the worm with second wing is fixed continuous.
Preferably, the worm is made of a hollow carbon rod, and electric wires respectively connected with the first motor and the second motor are arranged in the worm.
Preferably, be equipped with between the stationary vane with the first wing and be used for pegging graft the stationary vane with the first wing is in order to prevent the first electron bolt of the two relative rotations, the stationary vane with be equipped with between the second wing and be used for pegging graft the stationary vane with the second wing is in order to prevent the second electron bolt of the two relative rotations.
Preferably, the length of the first wing is 1/3-1/5 of the length of the fixed wing, and the length of the second wing is 1/3-1/5 of the length of the fixed wing.
Preferably, the stationary wing includes: the upper wing plate is a curved plate with an arched middle part, the lower wing plate is a flat plate, the same-direction edge parts of the upper wing plate and the lower wing plate are connected, the upper wing plate and the lower wing plate jointly enclose a supporting cavity with two open ends, and the reinforcing plate is connected with the upper wing plate and the lower wing plate.
Preferably, the reinforcing plates are arranged at intervals and are completely accommodated in the supporting cavity.
The utility model provides an unmanned aerial vehicle with wing mechanism verts, includes as above wing mechanism verts, unmanned aerial vehicle with wing mechanism verts still includes fuselage and fin unit, worm wheel and rotating electrical machines are all located in the fuselage.
Preferably, the center of gravity of the unmanned aerial vehicle with the tilt wing mechanism passes through the rotating shaft of the worm gear.
Preferably, the tail unit comprises a horizontal tail and a vertical tail which are fixedly connected with the body respectively, and the horizontal tail is provided with a tail motor.
Compared with the prior art, the unmanned aerial vehicle with the tilting wing mechanism can improve the stability of the unmanned aerial vehicle when the unmanned aerial vehicle is changed from vertical flight to horizontal flight, and can improve the wind resistance by adjusting the tilting angle of the rotating wing when the unmanned aerial vehicle suddenly encounters strong wind, so that the flight quality of the unmanned aerial vehicle with the tilting wing mechanism in the cruising process is ensured.
[ description of the drawings ]
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without inventive efforts,
wherein:
fig. 1 is a perspective view of one direction of a drone with tilt wing mechanism of the present invention (only solid lines shown);
fig. 2 is a perspective view of an alternative orientation of a drone with a tilt wing mechanism in accordance with the present invention;
fig. 3 is a perspective view of one direction of a drone with tilt wing mechanism of the present invention (also shown in phantom);
FIG. 4 is an enlarged view of a portion of FIG. 1 at A;
FIG. 5 is an enlarged view of a portion of FIG. 2 at B;
fig. 6 is a flow chart of a transition from multi-rotor to fixed-wing mode for a drone with a tilt-wing mechanism of the present invention.
In the figure:
1. the structure comprises a tilting wing mechanism, a body, a tail wing unit, a fixed wing, a first wing, a second wing, a rotating power unit, a first motor, a second motor, a first electronic bolt, a second electronic bolt, a horizontal tail wing, a vertical tail wing, a tail wing motor, an upper wing plate, a lower wing plate, a reinforcing plate, a supporting cavity and a lightening hole, wherein the tilting wing mechanism comprises 2, the body, 3, the tail wing unit, 11, the fixed wing, 12, the first wing, 13, the second wing, 14, the rotating power unit, 15, the first motor, 16, the second motor, 17, the first electronic bolt, 18, the second electronic.
[ detailed description ] embodiments
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-6, an unmanned aerial vehicle with a tilt wing mechanism comprises a tilt wing mechanism 1, and further comprises a fuselage 2 and a tail wing unit 3, wherein a worm gear and a rotating motor are arranged in the fuselage 2. The wing mechanism 1 that verts includes stationary vane 11 and locates the rotatory wing at the 11 both ends of stationary vane respectively, and the rotatory wing includes: first wing 12, second wing 13, stationary vane 11 and first wing 12 rotate and link to each other, and stationary vane 11 rotates with second wing 13 and links to each other, and the wing mechanism 1 that verts still includes the rotatory power unit 14 of the relative stationary vane 11 rotation of drive rotor, is equipped with first motor 15 on the first wing 12, is equipped with second motor 16 on the second wing 13.
In the embodiment, the unmanned aerial vehicle with the tilt wing mechanism adopts the unmanned aerial vehicle layout of the conventional fixed wing, has the fixed wing 11 with a large aspect ratio, and the fixed wing 11 is wide, so that good lift resistance is provided for the unmanned aerial vehicle with the tilt wing mechanism. The tail part of the body 2 is provided with a tail unit 3 for maintaining the balance of the flight. The tail unit 3 includes a horizontal tail 31 and a vertical tail 32 fixedly connected to the body 2, respectively, and a tail motor 33 is provided on the horizontal tail 31. The empennage motor 33 has low power and is used for maintaining the balance of the unmanned aerial vehicle with the tilt wing mechanism during vertical take-off and landing. The two ends of the fixed wing 11 with large aspect ratio are provided with a rotary wing which can rotate and comprises a first wing 12 and a second wing 13. The first wing 12 and the second wing 13 will turn upwards by 90 degrees in the taking-off and landing stage, so that the vertical taking-off and landing of the unmanned aerial vehicle with the tilting wing mechanism is realized. The power of the first motor 15 and the second motor 16 respectively mounted on the first wing 12 and the second wing 13 is relatively large, and the power is a main power system of the unmanned aerial vehicle with the tilt wing mechanism. The self weight of the unmanned aerial vehicle with the tilt wing mechanism is designed to be about 6kg, and the load is designed to be within 2kg, so that the maximum tension of each high-power motor reaches 4 kg. In the present embodiment, the first motor 15 and the second motor 16 are both QA-5308 motors.
Wherein: the rotary power unit 14 includes: worm wheel, worm, rotating electrical machines, fixed wing 11 below is located to the worm wheel, and the worm runs through in the both ends of fixed wing 11 and worm extend to first wing 12 and second wing 13 respectively along the length direction of fixed wing 11, and the worm rotates with fixed wing 11 and links to each other, and the worm links to each other with first wing 12 is fixed, and the worm links to each other with second wing 13 is fixed.
The rotary power unit 14 is used for realizing the rotation of the rotary wing, and the rotary motor and the worm gear are located inside the body 2 for realizing the rotation of the rotary wing. The worm wheel and the worm are meshed to form a transmission mechanism, a sleeve is arranged on the fixed wing 11 in the rotary power unit 14, the axis of the sleeve is aligned to the axis of the worm, the worm penetrates through the sleeve and the two ends of the worm to be connected with the rotary wing respectively, the worm is meshed with the worm wheel inside the machine body 2, and the rotary motor rotates to drive the worm wheel and the worm to rotate, so that the rotation of the rotary wing is realized. The rotation axis of worm wheel passes the focus of unmanned aerial vehicle that has the wing mechanism of verting. Namely, the position of the rotating shaft of the rotary wing during rotation is positioned on the axis of the gravity center of the whole aircraft, so that the unstable flight or difficult control of the aircraft caused by the imbalance problem during rotation of the rotary wing can be avoided. An electronic bolt is arranged between the rotary wing and the fixed wing 11, when the airplane flies from the vertical direction to the horizontal direction, the electronic bolt is popped up when the rotary wing part becomes the horizontal direction, the rotary wing is prevented from rotating, and the flying stability is improved.
More specifically, the worm is made of a hollow carbon rod, and electric wires are provided inside the worm to connect the first motor 15 and the second motor 16, respectively. The electric wires of the two propeller motors (the first motor 15 and the second motor 16) mounted on the rotary wing may be connected to a power source through a hollow carbon rod, and the propeller motors may be fixed to the carbon rod.
More specifically, a first electronic pin 17 for inserting the fixed wing 11 and the first wing 12 to prevent the fixed wing 11 and the first wing 12 from rotating relative to each other is disposed between the fixed wing 11 and the first wing 12, and a second electronic pin 18 for inserting the fixed wing 11 and the second wing 13 to prevent the fixed wing 11 and the second wing 13 from rotating relative to each other is disposed between the fixed wing 11 and the second wing 13. The electronic latch is installed at a connection portion with the rotary wing and the stationary wing 11, and the electronic latch is ejected when the rotary wing becomes horizontal, preventing the rotary wing from rotating. When the rotary wing needs to rotate, the electronic bolt is retracted, and the rotary wing can rotate freely.
More specifically, the length of the first wing 12 is 1/3-1/5 of the length of the stationary wing 11, and the length of the second wing 13 is 1/3-1/5 of the length of the stationary wing 11. More specifically, the rotating wing portions at both ends of the fixed wing 11 are 40% of the span length, which facilitates the rotation of the rotating wing.
More specifically, the stationary vane 11 includes: the supporting cavity comprises an upper wing plate 111, a lower wing plate 112 and a reinforcing plate 113, wherein the upper wing plate 111 is a curved plate with a middle part arched, the lower wing plate 112 is a flat plate, the same-direction edges of the upper wing plate 111 and the lower wing plate 112 are connected, the upper wing plate 111 and the lower wing plate 112 jointly enclose a supporting cavity 100 with two open ends, and the reinforcing plate 113 is connected with the upper wing plate 111 and the lower wing plate 112. The reinforcing plates 113 are arranged at intervals, and the reinforcing plates 113 are completely accommodated in the supporting cavity 100. The structure is beneficial to reducing the weight of the fixed wing 11 and simultaneously ensuring the width of the wing, thereby providing good lift resistance for the airplane.
When the unmanned aerial vehicle with the tilt wing mechanism is used, the rotation speeds of the three motors (the first motor 15, the second motor 16 and the empennage motor 33) are regulated and controlled through the electronic speed regulator, so that proper lift force and thrust force are provided for the unmanned aerial vehicle, and the attitude and the flight speed of the unmanned aerial vehicle with the tilt wing mechanism are finally controlled. The control process can be divided into three phases, namely a vertical take-off and landing phase, a transition phase between a multi-rotor wing and a fixed wing and a horizontal flight phase of the fixed wing.
(I) vertical take-off and landing stage
When the airplane takes off and lands vertically, the high-power motors (the first motor 15 and the second motor 16) turn upwards for a certain angle along with the rotating wings, and the rotating speed of the high-power motors is increased or reduced through the regulation and control of the electronic speed governor, so that enough lift force is provided for the airplane, and the low-power motors (the tail motor 33) on the tail wings are regulated and controlled, so that the low-power motors can provide balanced rotating force for the airplane. The three motors work together to finish vertical lifting.
Transition stage between multi-rotor and fixed wing
Fig. 6 is a flow chart of a mode of converting from a multi-rotor to a fixed wing, when the unmanned plane with the tilt wing mechanism of the invention is in a stage of hovering in the air, the power of three motors (the first motor 15, the second motor 16 and the tail wing motor 33) is regulated through an electronic speed regulator, and the tilting angle of the rotating wing can be controlled by controlling the action of the rotating motor, so that the unmanned plane with the tilt wing mechanism of the invention is in a horizontal flight state.
(III) horizontal flight
When the unmanned aerial vehicle with the tilting wing mechanism horizontally cruises, the aircraft flies at an approximately constant speed, the thrust tilts forwards, the rotating wing changes to be in the horizontal direction, and meanwhile, the fixed wing 11 and the rotating wing bear part or all of the lift force. At the moment, the low-power motor of the tail wing is turned off, and the high-power motor can change the rotating speed under the regulation and control of the electronic speedometer so as to change the flying speed of the airplane.
Compared with the related art, the invention has the following beneficial effects:
1. vertical take-off and landing are realized through the rotating wings, the stress of the steering engine is reduced, and the energy consumption is reduced
The existing tilt rotor wing technology adopts a tilt motor mode, but a steering engine is always in a stressed state in the flight process, and the tilt rotor wing structure is adopted in the invention, so that the steering engine is in the stressed state only in vertical take-off and landing. When the rotating wing of the unmanned aerial vehicle becomes horizontal, the steering engine is in an unstressed state. Because the motion steering engine does not need to bear locking torque and only works in the tilting process, the service life of the steering engine is greatly prolonged, and the overall reliability of the unmanned aerial vehicle is also greatly improved; in addition, the steering engine is in an unstressed state during flying before the horizontal direction, so that the steering engine can not be electrified to work, and the power consumption of the steering engine is greatly reduced.
2. Proper aspect ratio of rotary wing
The proportion of the existing rotary wing part in the whole wing is not very suitable, the rotary part is selected to account for 40% of the span length, and the rotary parts at the left end and the right end are 1050mm respectively. The problem that the aircraft is difficult to control due to the fact that the rotary wing is large in size and large in resistance when rotating is effectively solved, and the problem that the rotary wing is small in size and can bear large resistance when flying vertically is solved.
3. The rotary wing is of a hollow structure, so that the utilization rate of the mechanism is improved
The rotary wing is of a hollow structure, and the adapter is arranged in the tilting shaft in a penetrating mode and is fixedly connected with the tilting shaft through a bolt. Through setting the rotor wing to hollow structure, can reduce the weight of the axle that verts on the one hand, on the other hand can wear to establish from fuselage 2 to the power supply wire and the data transmission line of the wing mechanism 1 that verts and arrange in the axle that verts, has improved the utilization ratio of mechanism for whole unmanned aerial vehicle structure that has the wing mechanism that verts is more succinct, and effective reduce cost.
4. Using worm-and-gear arrangements to effect rotation of wings
The rotary wing is of a hollow structure, a worm fixedly connected with the rotary wings at two ends is coupled with a worm wheel in the machine body 2 through a sleeve on the axis of the fixed wing 11, the worm is driven by a motor, electric wires of two propeller motors arranged on the rotary wing are connected with a power supply through a hollow carbon rod, and the propeller motors can also be fixed on the carbon rod. The stability of the rotating wing steering is improved.
5. Stability of unmanned aerial vehicle is improved to chooseing for use electronic bolt design
An electronic bolt is installed between the rotary wing and the fixed wing 11, because the rotary wing needs to become horizontal when the airplane changes from vertical flight to horizontal flight, in order to ensure the stability of horizontal flight, the electronic bolt is installed between the rotary wing and the fixed wing 11, so as to prevent the rotation under the influence of resistance, and improve the stability of flight.
6. The invention can realize the stable flight of the unmanned aerial vehicle by adjusting the tilt angle of the fixed wing and the rotary wing
The tilt angle of the fixed wing 11 and the rotary wing is adjusted and adjusted according to the state of the unmanned aerial vehicle through flight control, coupling influence, energy loss and a plurality of indexes such as overshoot during transition completion are comprehensively considered, an optimal tilt angle curve is obtained, and the flight quality of the unmanned aerial vehicle with the tilt wing mechanism in the transition process is improved.
From the above, the unmanned aerial vehicle with the tilt wing mechanism has the advantages of long endurance time of a fixed wing aircraft, high hovering efficiency of a multi-rotor aircraft, strong flying maneuverability and the like, and the design of the rotary wing can realize vertical take-off and landing, so that the requirements of the existing fixed wing on take-off and landing conditions are greatly reduced. The design of the rotary wing of the unmanned aerial vehicle with the tilt wing mechanism well overcomes the defects of weak wind resistance, short endurance time, always stressed state of the steering engine and the like caused by the design of the existing tilt motor, and can realize that the steering engine is in the stressed state only when the unmanned aerial vehicle vertically takes off and lands, thereby greatly reducing the power consumption of the steering engine. The service life of the steering engine is greatly prolonged when the unmanned aerial vehicle is in an unstressed state for a long time, and the overall reliability of the unmanned aerial vehicle is greatly improved; the electronic bolt, the flight control adjusting tilting angular speed, the small-power motor on the horizontal wing of the tail and the like are designed, so that the stability of the unmanned aerial vehicle can be improved when the unmanned aerial vehicle flies from the vertical direction to the horizontal direction, the wind resistance can be improved by adjusting the tilting angle of the rotary wing when the unmanned aerial vehicle suddenly encounters strong wind, and the flight quality of the unmanned aerial vehicle with the tilting wing mechanism in the cruising process is ensured.
While the foregoing is directed to embodiments of the present invention, it will be understood by those skilled in the art that various changes may be made without departing from the spirit and scope of the invention.
Claims (10)
1. The utility model provides a wing mechanism verts, its characterized in that includes the stationary vane and locates respectively the rotary wing at stationary vane both ends, the rotary wing includes: the tilting wing mechanism comprises a first wing and a second wing, wherein the fixed wing is connected with the first wing in a rotating mode, the fixed wing is connected with the second wing in a rotating mode, the tilting wing mechanism further comprises a drive, the rotating wing is opposite to the rotating power unit of the fixed wing, a first motor is arranged on the first wing, and a second motor is arranged on the second wing.
2. The drone with tilt wing mechanism of claim 1, wherein the rotary power unit includes: worm wheel, worm, rotating electrical machines, the worm wheel is located the stationary vane below, the worm is followed the length direction of stationary vane runs through the stationary vane just the both ends of worm extend to respectively in first wing and the second wing, the worm with the stationary vane rotates and links to each other, the worm with first wing is fixed continuous, the worm with second wing is fixed continuous.
3. The drone with tilt wing mechanism according to claim 2, wherein the worm is made of hollow carbon rod, inside which are wires connecting the first and second motors, respectively.
4. The UAV having a tilt wing mechanism according to claim 3 wherein a first electrical connector for connecting the stationary wing to the first wing to prevent relative rotation therebetween is disposed between the stationary wing and the first wing, and a second electrical connector for connecting the stationary wing to the second wing to prevent relative rotation therebetween is disposed between the stationary wing and the second wing.
5. The drone with tilt wing mechanism of claim 4, wherein the first wing has a length 1/3-1/5 of the fixed wing length and the second wing has a length 1/3-1/5 of the fixed wing length.
6. The drone with tilt wing mechanism of claim 5, wherein the fixed wing includes: the upper wing plate is a curved plate with an arched middle part, the lower wing plate is a flat plate, the same-direction edge parts of the upper wing plate and the lower wing plate are connected, the upper wing plate and the lower wing plate jointly enclose a supporting cavity with two open ends, and the reinforcing plate is connected with the upper wing plate and the lower wing plate.
7. The UAV having a tilt wing mechanism of claim 6 wherein the reinforcing plate is spaced apart and is fully received in the cavity.
8. An unmanned aerial vehicle with a tilt wing mechanism, comprising the tilt wing mechanism of any one of claims 1-7, further comprising a fuselage and a tail unit, wherein the worm gear and the rotating motor are both disposed in the fuselage.
9. The drone with tilt wing mechanism according to claim 8, wherein the rotation axis of the worm gear passes through the center of gravity of the drone with tilt wing mechanism.
10. The UAV having a tilt wing mechanism of claim 9, wherein the tail unit comprises a horizontal tail and a vertical tail fixedly connected to the fuselage, respectively, the horizontal tail having a tail motor thereon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010923570.3A CN112009674A (en) | 2020-09-04 | 2020-09-04 | Tilt wing mechanism and have unmanned aerial vehicle of tilt wing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010923570.3A CN112009674A (en) | 2020-09-04 | 2020-09-04 | Tilt wing mechanism and have unmanned aerial vehicle of tilt wing mechanism |
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Cited By (1)
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| WO2022206852A1 (en) * | 2021-04-02 | 2022-10-06 | 深圳市道通智能航空技术股份有限公司 | Tiltable wing and unmanned aerial vehicle |
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