CN113665804A - Rotor angle adjustable unmanned aerial vehicle - Google Patents
Rotor angle adjustable unmanned aerial vehicle Download PDFInfo
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- CN113665804A CN113665804A CN202111103086.7A CN202111103086A CN113665804A CN 113665804 A CN113665804 A CN 113665804A CN 202111103086 A CN202111103086 A CN 202111103086A CN 113665804 A CN113665804 A CN 113665804A
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- 230000007246 mechanism Effects 0.000 claims description 10
- 238000010586 diagram Methods 0.000 description 10
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
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- 238000006467 substitution reaction Methods 0.000 description 1
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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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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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
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The unmanned aerial vehicle with the adjustable rotor wing angle comprises a body, a central wing and a plurality of tail support rods, wherein a rotary power cabin is arranged at the front end of each tail support rod; the rotary power cabin comprises a first rotor wing assembly and a first movable assembly of a first movable assembly, wherein the first movable assembly comprises a driving device and a rotating part. When unmanned aerial vehicle need realize VTOL and hang and stop, first rotor subassembly rotates certain angle to make first rotor spare for unmanned aerial vehicle's VTOL or hover and provide the power of vertical direction, when unmanned aerial vehicle need not carry out VTOL or hover, first rotor subassembly rotates to initial position, for unmanned aerial vehicle provides the power of horizontal direction, makes rotor angle adjustable, provides the power of equidirectional not for unmanned aerial vehicle.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to an unmanned aerial vehicle with an adjustable rotor wing angle.
Background
With the development of economy, the application of general aviation flight appliances, especially unmanned aerial vehicles, is more and more extensive. The unmanned aerial vehicle can be used in general aviation fields such as aerial photography, surveying and mapping and cargo delivery, and has wide application prospect.
At present, the unmanned aerial vehicle that is used for general aviation field on the market mainly is fixed wing unmanned aerial vehicle, and fixed wing unmanned aerial vehicle load is great, nevertheless need provide long runway and spacious place in order to take off and land, can't realize VTOL or hover, need provide one kind for general aviation field and can realize VTOL or hover's unmanned aerial vehicle.
Disclosure of Invention
The invention mainly aims to provide an unmanned aerial vehicle which enables a rotor wing to be adjustable in angle so as to realize vertical take-off, landing and hovering.
In order to achieve the main purpose, the unmanned aerial vehicle with the adjustable rotor wing angle comprises a fuselage, a central wing and a plurality of tail support rods, wherein the central wing is arranged on the fuselage, the tail support rods are arranged on the central wing, and a rotary power cabin is arranged at the front end of each tail support rod; the rotary power cabin comprises a first rotor wing assembly and a first movable assembly, a rotating frame of the first rotor wing assembly is rotatably connected to a fixed frame of the first movable assembly, and a first rotor wing piece of the first rotor wing assembly is connected to the rotating frame; the first movable assembly comprises a driving device and a rotating part, the driving device is arranged between the first fixing plate and the second fixing plate of the fixing frame, the first part of the rotating part is connected to the rotating part of the driving device, and the second part of the rotating part is fixedly connected to the driven plate of the rotating frame.
By the above scheme, the rotary power cabin has been arranged to the front end of each tail vaulting pole, fixed rotor mechanism has been arranged to the rear end of each tail vaulting pole, unmanned aerial vehicle need realize VTOL and hang when stopping, drive arrangement drives and rotates the piece and rotate, it drives the rotating turret and rotates, the rotating turret drives first rotor subassembly and rotates certain angle, thereby make first rotor spare for unmanned aerial vehicle's VTOL or hover and provide the power of vertical direction, when unmanned aerial vehicle need not carry out VTOL or hover, first rotor subassembly rotates to initial position, provide the power of horizontal direction for unmanned aerial vehicle, make rotor angle adjustable, provide the power of equidirectional not for unmanned aerial vehicle.
Preferably, the driving device is a servo motor, and the rotating part is a rotor of the driving device.
Furthermore, the fixing part of the driving device is a stator of the servo motor, and the fixing part is fixedly connected to the first fixing plate.
Furthermore, the first movable assembly comprises a first rotating shaft, and the first rotating shaft penetrates through the rotating part, the rotating frame, the fixed frame and the driving device.
Furthermore, the rotating part is a step-shaped hollow cylinder, and the first part and the second part are coaxially arranged.
Furthermore, the second part is positioned at the outer side of the driven plate, the first part penetrates through the driven plate and the second fixed plate, and the first part is inserted into the rotating part.
Furthermore, a connecting plate of the rotating frame is abutted against the first fixing plate, and the connecting plate is communicated with the inside of the first fixing plate; the first fixed plate, the second fixed plate, the driven plate and the connecting plate are all semi-waist-shaped plates.
Further, outer wings are arranged at two ends of the central wing respectively, the outer wings are rotatably connected to the central wing, and each outer wing is provided with a second rotor assembly.
Furthermore, the unmanned aerial vehicle comprises a second movable assembly, the second movable assembly comprises a second rotating shaft, a rocker arm and a push rod assembly, one part of the second rotating shaft is fixedly inserted into the outer wing, one part of the second rotating shaft is movably inserted into the central wing, and the second rotating shaft is fixedly inserted into the rocker arm; the installed part of push rod subassembly is connected in unmanned aerial vehicle's rib connecting piece, and rib connecting piece connects in the first rib and the second rib of outer wing, and the first bulb of the electric push rod portion of push rod subassembly is connected in the installed part, and the second bulb of electric push rod portion is connected in the rocking arm.
Furthermore, a fixed rotor wing mechanism is arranged at the rear end of each tail stay bar, the second rotor wing assembly comprises a second rotor wing piece, a motor base and a second rotor wing connecting piece, the second rotor wing piece is arranged on the motor base, the motor base is connected to the second rotor wing connecting piece, and the second rotor wing connecting piece is connected to the first wing rib; the unmanned aerial vehicle also comprises a nose landing gear, a main landing gear and an empennage, wherein the nose landing gear, the main landing gear and the empennage are uniformly arranged on the body of the unmanned aerial vehicle; the rotary power cabin comprises a power supply part, a first electric controller and a second electric controller, wherein the power supply part is fixed in the tail stay bar, the first electric controller and the second electric controller are uniformly distributed in the tail stay bar, the power supply part is electrically connected to the first electric controller and the second electric controller, the first electric controller is electrically connected to the driving device, and the second electric controller is electrically connected to the rotor motor of the first rotor assembly.
Drawings
The invention is further illustrated by means of the attached drawings, but the embodiments in the drawings do not constitute any limitation to the invention, and for a person skilled in the art, other drawings can be derived on the basis of the following drawings without inventive effort.
Fig. 1 is a structural diagram of a first embodiment of an unmanned aerial vehicle according to the present invention.
Fig. 2 is a partial exploded view of a first embodiment of the drone of the present invention.
Fig. 3 is a partial structural diagram of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 4 is an exploded view of the structure shown in fig. 3.
Fig. 5 is a structural diagram of a turret of a first embodiment of the drone according to the present invention.
Fig. 6 is a structural diagram of a fixing frame of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 7 is a structural diagram of a rotating member of the first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 8 is a partial structural view of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 9 is a partial exploded view of a first embodiment of a drone according to the invention.
Fig. 10 is a partial structural view of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 11 is a partial structural view of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 12 is a partial structural view of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 13 is a partial structural view of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 14 is an exploded view of the structure shown in fig. 13.
Fig. 15 is a partial structural view of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 16 is a partial structural view of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 17 is a partial structural view of a first embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 18 is a structural diagram of a first embodiment of the drone according to the invention.
Fig. 19 is a structural diagram of a second embodiment of the drone according to the invention.
Fig. 20 is a block diagram of a second embodiment of a drone according to the invention.
Fig. 21 is a structural diagram of a third embodiment of the unmanned aerial vehicle according to the present invention.
Fig. 22 is a block diagram of a third embodiment of the drone according to the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
First embodiment
Referring to fig. 1 and 2, the unmanned aerial vehicle with adjustable rotor angle provided by this embodiment includes fuselage 1, outer wing, central wing 4 and a plurality of tail stay bars, the outer wing has been arranged respectively at the both ends of central wing 4, the outer wing that is located the right-hand member of central wing 4 is outer wing 2 shown in the drawing, the outer wing that is located the left end of central wing 4 is outer wing 3 shown in the drawing, outer wing 2 and outer wing 3 are mutual mirror symmetry and arrange, central wing 4 arranges in fuselage 1. In this embodiment, the quantity of tail vaulting pole is two, the tail vaulting pole that is located fuselage 1 right side is shown in the drawing tail vaulting pole 5, the tail vaulting pole that is located fuselage 1 left side is shown in the drawing tail vaulting pole 6, the tail vaulting pole is arranged in central wing 4, unmanned aerial vehicle still includes nose landing gear 7, main undercarriage 8 and fin 9, nose landing gear 7, main undercarriage 8 and fin 9 equipartition are arranged in fuselage 1, nose landing gear 7 realizes unmanned aerial vehicle's the taxiing and turns to, main undercarriage 8 realizes unmanned aerial vehicle's the speed reduction that slides, fin 9 is the V type.
Referring to fig. 1-8, each outer wing has a second rotor assembly disposed thereon, second rotor assembly 10 is disposed on outer wing 2 as shown, second rotor assembly 13 is disposed on outer wing 3 as shown, second rotor assembly 13 is identical in structure to second rotor assembly 12, and outer wing 2 and outer wing 3 are mirror images of each other.
The front end of each tail brace rod is provided with a rotary power cabin, the rotary power cabin 11 is arranged on the tail brace rod 5 shown in the figure, and the rotary power cabin 12 is arranged on the tail brace rod 6 shown in the figure.
A fixed rotor mechanism is arranged at the rear end of each tail stay, a fixed rotor mechanism 15 is arranged at the tail stay 5 shown in the figure, and a fixed rotor mechanism 14 is arranged at the tail stay 6 shown in the figure.
The rotary power cabin 12 includes a first rotor assembly and a first movable assembly, the rotating frame 19 of the first rotor assembly is rotatably connected to the fixed frame 20 of the first movable assembly, the first rotor part 121 of the first rotor assembly is connected to the rotating frame 19 in a threaded manner, the rotating shell 23 of the first rotor assembly is connected to the propeller 122 of the first rotor part 121 in a clamped manner, the first rotor part 121 is provided with a rotor motor, and the rotor shell 22 is arranged outside the rotor motor.
The first movable assembly includes a driving device 21, a rotation member 24, the driving device 21 is disposed between the first fixing plate 201 and the second fixing plate 202 of the fixing frame 20, the first portion 241 of the rotation member 24 is screw-coupled to the rotation portion 27 of the driving device 21, and the second portion 242 of the rotation member 24 is detachably fixed to the driven plate 191 of the rotating frame 19 by screw-coupling.
The drive unit 21 is a servo motor, and the rotating unit 27 is a rotor of the drive unit 21.
The fixing portion 26 of the driving device 21 is a stator 26 of the servo motor, and the fixing portion 26 is detachably fixed to the first fixing plate 201 by screwing.
The first movable assembly includes a first rotating shaft 25, and the first rotating shaft 25 passes through the rotating member 24, the rotating frame 19, the fixed frame 20 and the driving device 21.
The rotating member 24 is a stepped hollow cylinder, and the first portion 241 and the second portion 242 are coaxially disposed.
The second portion 242 is positioned outside the receiving plate, the first portion 241 passes through the receiving plate 191 and the second fixing plate 202, and the first portion 241 is inserted into the rotating portion 27.
Further, the connection plate 192 of the rotating frame 19 abuts on the first fixed plate 201, the connection plate 192 and the inside of the first fixed plate 201 communicate with each other, and the first fixed plate 201, the second fixed plate 202, the driven plate 191, and the connection plate 192 are all half waist-shaped plates.
Referring to fig. 9 to 11, the rotary power compartment 12 includes a power supply element 123, a first electronic module 124 and a second electronic module 125, the power supply element 123 is fixed in the tail stay, the first electronic module 124 and the second electronic module 125 are uniformly disposed in the tail stay 5, the power supply element 123 is electrically connected to the first electronic module 124 and the second electronic module 125, the first electronic module 124 is electrically connected to the driving device 21, and the second electronic module 125 is electrically connected to the rotor motor of the first rotor assembly.
The outer wing 2 is rotatably connected to the central wing 4.
Referring to fig. 12 to 17, the drone includes a second movable assembly, the second movable assembly includes a second rotating shaft 37, a rocker arm 38 and a push rod assembly 41, a portion of the second rotating shaft 37 is fixedly inserted into the first rib 32 and the second rib 33 of the outer wing 2, a portion of the second rotating shaft 37 is movably inserted into the rib 35 and the rib 36 of the central wing 4, and the wing 39 and the wing 40 of the central wing 4 are connected to the rib 35 and the rib 36. A portion of the second rotation shaft 37 may be fixedly inserted into the first rib 32 and the second rib 33 of the outer wing 2 by interference fit, or a portion of the second rotation shaft 37 may be detachably fixedly connected to the first rib 32 and the second rib 33 by snap-fit, screw-connection. The second rotating shaft 37 is fixedly inserted into the rocker arm 38, and the second rotating shaft 37 may be fixedly inserted into the rocker arm 38 by interference fit.
The mounting part 42 of the push rod assembly 41 is connected to the rib connecting piece 34 of the unmanned aerial vehicle, the rib connecting piece 34 is connected to the first rib 32 and the second rib 33 of the outer wing 2, the first ball head of the electric push rod part 44 of the push rod assembly 41 is connected to the mounting part 42, and the second ball head of the electric push rod part 44 is connected to the rocker arm 38.
The front end of each tail stay bar is provided with a rotary power cabin 12, the rear end of each tail stay bar is provided with a fixed rotor wing mechanism, when the unmanned aerial vehicle needs to realize vertical take-off, landing and suspension, the driving device 21 drives the rotating piece 24 to rotate, the rotating piece 24 drives the rotating frame 19 to rotate, the rotating frame 19 drives the first rotor wing assembly to rotate by a certain angle, the first rotor wing assembly can rotate by 90 degrees, so that the first rotor wing assembly 121 provides vertical power for the unmanned aerial vehicle during vertical take-off, landing or suspension, at the moment, the unmanned aerial vehicle is in a rotor wing flight mode, fig. 8 can be seen, fig. 9 and 18 can be seen, moreover, the push rod assembly 41 drives the rocker arm 38 to rotate, the rocker arm 38 drives the second rotating shaft 37 to rotate, the second rotating shaft 37 can drive the outer wing to rotate by 90 degrees, so that the second rotor wing assembly provides vertical power assistance for the unmanned aerial vehicle in the rotor wing flight mode; when unmanned aerial vehicle need not take off and land perpendicularly or hover, first rotor subassembly rotates to initial position, and the second rotor subassembly rotates to initial position, for unmanned aerial vehicle provides the power of horizontal direction, and unmanned aerial vehicle is in fixed wing flight mode this moment, and visible figure 1 consequently makes rotor angle adjustable, for unmanned aerial vehicle provides the power of equidirectional, unmanned aerial vehicle can adopt rotor flight mode to take off and land, needn't build the runway for unmanned aerial vehicle's taking off and land.
The servo motor and the electric push rod are used as the rotary power of the rotor wing, so that the rotary mechanism has the characteristics of high control precision, strong overload resistance and the like, and the design of the rotary mechanism can be simplified.
First rotor subassembly all uses same screw motor at rotor flight mode and fixed wing flight mode, can reduce air resistance and invalid weight to increase the time of flight and energy efficiency ratio.
In this embodiment, the quantity of tail vaulting pole is two, and unmanned aerial vehicle is six rotor configurations.
Unmanned aerial vehicle adopts the integrative design of modularization, all adopts the quick dismantlement mode between each part.
The six-rotor layout is adopted in the embodiment, the safety is high, and when individual motors fail, the remaining motors can balance the airplane until safe landing. The rotor motor impels efficiently, and when unmanned aerial vehicle VTOL, 4 rotors in wing leading edge are rotatory 90 degrees, and with two motors in rear power jointly, light take off and land, trun into the fixed wing after, 4 motor work in wing leading edge, two motors in back stall, improve propulsive efficiency.
Unmanned aerial vehicle's driving system is become by lithium cell or hydrogen fuel cell, motor, electricity accent, and full quick-witted pure electric drive, to zero pollution of environment, and the flight noise is low, improves the travelling comfort.
In particular, the rotary power pods can be used as modular components, and the number of the rotary power pods is determined by a user according to a specific application scene of the unmanned aerial vehicle.
Second embodiment
Referring to fig. 19 and 20, in this embodiment, the unmanned aerial vehicle adopts a four-rotor configuration, the second rotor assembly arranged on the outer wing is not adopted in this embodiment, the number of the tail stays 5 is two, the rotary power cabin 12 is arranged at the front end of each tail stay 5, and the rest of the structure is the same as that of the first embodiment, and is not described again here.
Third embodiment
Referring to fig. 21 and 22, in this embodiment, the unmanned aerial vehicle adopts an eight-rotor configuration, the second rotor assembly arranged on the outer wing is not adopted in this embodiment, the number of the tail struts 5 is four, the rotary power cabin 12 is arranged at the front end of each tail strut 5, and the rest of the structure is the same as that of the first embodiment, and is not described again here.
The embodiment of a modification is that the unmanned aerial vehicle adopts an eight-rotor configuration, adopts a second rotor assembly arranged on the outer wing, the number of the tail stay rods 5 is four, the front end of each tail stay rod 5 is provided with a rotary power cabin 12, and other structures are the same as those of the first embodiment and are not described again.
Finally, it should be emphasized that the present invention is not limited to the above-described embodiments, but only the preferred embodiments of the invention have been described above, and the present invention is not limited to the above-described embodiments, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides an unmanned aerial vehicle of rotor angularly adjustable, includes fuselage, central authorities ' wing and a plurality of tail vaulting pole, the central authorities ' wing arrange in the fuselage, the tail vaulting pole is arranged in the central authorities ' wing, its characterized in that:
a rotary power cabin is arranged at the front end of each tail stay bar, and a fixed rotor wing mechanism is arranged at the rear end of each tail stay bar;
the rotary power cabin comprises a first rotor wing assembly and a first movable assembly, a rotating frame of the first rotor wing assembly is rotatably connected to a fixed frame of the first movable assembly, and a first rotor wing piece of the first rotor wing assembly is connected to the rotating frame;
the first movable assembly comprises a driving device and a rotating part, the driving device is arranged between the first fixing plate and the second fixing plate of the fixing frame, the first part of the rotating part is connected to the rotating part of the driving device, and the second part of the rotating part is fixedly connected to the driven plate of the rotating frame.
2. The unmanned aerial vehicle with adjustable rotor angle of claim 1, wherein:
the driving device is a servo motor, and the rotating part is a rotor of the driving device.
3. An unmanned aerial vehicle with adjustable rotor angle according to claim 2, wherein:
the fixing part of the driving device is the stator of the servo motor and is fixedly connected with the first fixing plate.
4. An unmanned aerial vehicle with adjustable rotor angle according to claim 3, wherein:
the first movable assembly comprises a first rotating shaft, and the first rotating shaft penetrates through the rotating part, the rotating frame, the fixed frame and the driving device.
5. The unmanned aerial vehicle with adjustable rotor angle of claim 4, wherein:
the rotating piece is a stepped hollow cylinder, and the first portion and the second portion are coaxially arranged.
6. An unmanned aerial vehicle with adjustable rotor angle according to claim 5, wherein:
the second portion is located outside the driven plate, the first portion passes through the driven plate and the second stationary plate, and the first portion is inserted into the rotating portion.
7. The unmanned aerial vehicle with adjustable rotor angle of claim 6, wherein:
the connecting plate of the rotating frame abuts against the first fixing plate, and the connecting plate is communicated with the inside of the first fixing plate;
the first fixing plate, the second fixing plate, the driven plate and the connecting plate are all semi-waist-shaped plates.
8. An unmanned aerial vehicle with adjustable rotor angle according to any one of claims 1 to 7, wherein:
outer wings have been arranged respectively at the both ends of central authorities 'wing, outer wing rotationally connect in the central authorities' wing, each outer wing has arranged the second rotor subassembly.
9. An unmanned aerial vehicle with adjustable rotor angle according to claim 8, wherein:
the unmanned aerial vehicle comprises a second movable assembly, the second movable assembly comprises a second rotating shaft, a rocker arm and a push rod assembly, one part of the second rotating shaft is fixedly inserted into the outer wing, one part of the second rotating shaft is movably inserted into the central wing, and the second rotating shaft is fixedly inserted into the rocker arm;
push rod assembly's installed part connect in unmanned aerial vehicle's rib connecting piece, rib connecting piece connect in the first rib and the second rib of outer wing, push rod assembly's electric push rod portion's first bulb connect in the installed part, electric push rod portion's second bulb connect in the rocking arm.
10. An unmanned aerial vehicle with adjustable rotor angle according to claim 9, wherein:
the rear end of each tail stay bar is provided with a fixed rotor wing mechanism,
the second rotor assembly comprises a second rotor piece, a motor base and a second rotor connecting piece, the second rotor piece is arranged on the motor base, the motor base is connected to the second rotor connecting piece, and the second rotor connecting piece is connected to the first rib;
the unmanned aerial vehicle also comprises a nose landing gear, a main landing gear and an empennage, wherein the nose landing gear, the main landing gear and the empennage are uniformly distributed on the body, the nose landing gear realizes the sliding steering of the unmanned aerial vehicle, the main landing gear realizes the sliding deceleration of the unmanned aerial vehicle, and the empennage is V-shaped;
the rotary power cabin comprises a power supply part, a first electric regulator and a second electric regulator, the power supply part is fixed in the tail stay bar, the first electric regulator and the second electric regulator are uniformly distributed on the tail stay bar,
the power supply part is electrically connected with the first electric controller and the second electric controller, the first electric controller is electrically connected with the driving device, and the second electric controller is electrically connected with a rotor motor of the first rotor assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111103086.7A CN113665804A (en) | 2021-09-18 | 2021-09-18 | Rotor angle adjustable unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111103086.7A CN113665804A (en) | 2021-09-18 | 2021-09-18 | Rotor angle adjustable unmanned aerial vehicle |
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| CN113665804A true CN113665804A (en) | 2021-11-19 |
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| CN202111103086.7A Pending CN113665804A (en) | 2021-09-18 | 2021-09-18 | Rotor angle adjustable unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114655434A (en) * | 2022-05-25 | 2022-06-24 | 中国空气动力研究与发展中心空天技术研究所 | Automatic angle changing device for tail-pushing motor of vertical take-off and landing composite wing unmanned aerial vehicle |
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| CN113044212A (en) * | 2019-12-26 | 2021-06-29 | 中国科学院沈阳自动化研究所 | Medium-sized tilt rotor unmanned aerial vehicle |
| CN111169631A (en) * | 2020-02-21 | 2020-05-19 | 山东蜂巢航空科技有限公司 | Rotor unmanned aerial vehicle verts |
| CN111661361A (en) * | 2020-05-08 | 2020-09-15 | 珠海天晴航空航天科技有限公司 | Fast assembly's unmanned aerial vehicle |
| CN213008725U (en) * | 2020-06-05 | 2021-04-20 | 沈阳无距科技有限公司 | Unmanned aerial vehicle's motor device and unmanned aerial vehicle that verts |
Cited By (1)
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| CN114655434A (en) * | 2022-05-25 | 2022-06-24 | 中国空气动力研究与发展中心空天技术研究所 | Automatic angle changing device for tail-pushing motor of vertical take-off and landing composite wing unmanned aerial vehicle |
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