CN114180046A - Electric vertical take-off and landing unmanned aerial vehicle - Google Patents
Electric vertical take-off and landing unmanned aerial vehicle Download PDFInfo
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- CN114180046A CN114180046A CN202111542722.6A CN202111542722A CN114180046A CN 114180046 A CN114180046 A CN 114180046A CN 202111542722 A CN202111542722 A CN 202111542722A CN 114180046 A CN114180046 A CN 114180046A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
Abstract
The invention discloses an electric vertical take-off and landing unmanned aerial vehicle, which comprises a body, wherein a plurality of body ducts are symmetrically arranged on the body along the axial direction of the body, wing tip duct fans are arranged on wings at two sides of the body, the body duct fans are installed in the body ducts, a load compartment is arranged between the body ducts, the wing tip duct fans are arranged at wing tips and are rotationally connected with the wings, the body duct fans and the wing tip duct fans are driven by electric power, the rotating speeds and the blade pitches of the body duct fans and the wing tip duct fans can be adjusted, and the wing tip duct fans change the flight attitude of the unmanned aerial vehicle in a manner of rotating relative to the wings. The aircraft of the invention innovatively optimizes the layout design of the tilt ducted fan and the fixed wings, realizes the vertical take-off and landing functions, has the characteristics of high flight speed and low noise, has lower manufacturing cost, is favorable for marketization and overcomes the problems in the prior art.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an electric vertical take-off and landing unmanned aerial vehicle.
Background
As an important component in the field of aircrafts, the development of an electric vertical take-off and landing aircraft (eVTOL) is more and more rapid, and the eVTOL electric vertical take-off and landing aircraft has the advantages of vertical take-off and landing and air flight, is expected to take off from a take-off and landing site in a city and reach a destination after crossing ground traffic in the future, and can further solve the problem of urban ground congestion. A common solution is a multi-rotor aircraft, which can take off and land independently and vertically without being limited by the field, but its blades always provide an upward lift force, the forward flying power is provided by the horizontal component after tilting, which is limited by the passenger's riding experience, and the tilt angle is necessarily limited, so its flying speed is low, and at the same time, the blades are exposed, the noise is slightly large, and they are approximately in the same plane with the passengers, increasing the safety risk of the passengers. Use Joby company eVTOL as another class of tilt rotor aircraft of representative to avoid the partial shortcoming of many rotors, the tilt rotor of this kind of aircraft upwards provides lift when VTOL, high-speed flight attitude down verts and provides the pulling force to the level, lift is provided by the wing completely, can take into account the high characteristics of fixed wing flying speed when VTOL, but the configuration overall arrangement that all has the propeller in development or release on the market arranges unreasonable shortcoming for tilting mechanism complexity and structure weight increase by a wide margin. Even if the eVTOL is used as an unmanned aerial vehicle, the problems of low flying speed, high noise, complex mechanism and the like exist, and the eVTOL is difficult to compete with the traditional inorganic aircraft.
Disclosure of Invention
The invention aims to: aiming at the existing problems, the invention provides an electric vertical take-off and landing unmanned aerial vehicle, the aircraft of the invention innovatively carries out the optimized layout design of the tilting ducted fan and the fixed wings, realizes the vertical take-off and landing function, has the characteristics of high flight speed and low noise, has lower manufacturing cost, is beneficial to marketization and overcomes the problems in the prior art.
The technical scheme adopted by the invention is as follows: the utility model provides an electronic VTOL unmanned vehicles, includes the fuselage, along the axis direction of fuselage, the symmetry is provided with a plurality of fuselage ducts on the fuselage, is provided with wing tip duct fan on the wing of fuselage both sides, install fuselage duct fan in the fuselage duct, be the load cabin between the fuselage duct, wing tip duct fan sets up in wing tip department, and rotates with the wing and be connected, fuselage duct fan and wing tip duct fan all drive through electric power, and the rotational speed and the pitch homoenergetic of fuselage duct fan and wing tip duct fan are adjusted to control unmanned vehicles's lift, wing tip duct fan changes unmanned vehicles's flight gesture through the mode for wing pivoted.
Further, the fuselage duct sets up to 2, the fuselage duct fan includes one deck paddle group at least, paddle group comprises a plurality of paddles that are on the coplanar, the stiff end and the axial hinge of paddle are connected, axial hinge and propeller hub fixed connection, propeller hub and brushless motor's output shaft fixed connection, brushless motor pass through the casing fixed connection of a supporting beam with the fuselage, brushless motor's electric power input end and the power switch-on that is located the fuselage, and brushless motor's output shaft rotates and drives the axial hinge and rotate, and then drives paddle group and rotate.
Furthermore, the supporting beam is a cross-shaped tubular beam, the brushless motor is fixedly installed in the center of the cross-shaped tubular beam, and the cross-shaped tubular beam is fixedly connected with the machine body shell to form a bearing support to support the machine body ducted fan.
Further, a movable ring and a fixed ring are sleeved on an output shaft of the brushless motor and located below the propeller hub, the movable ring is fixed on the output shaft of the brushless motor through a flat key and rotates along with the output shaft of the brushless motor, a certain margin is reserved on a key groove of the output shaft of the brushless motor, the movable ring can slide up and down relative to the output shaft, the fixed ring and the movable ring form a rolling bearing assembly through a rolling body, and the outer side of the fixed ring is connected with the cross pipe beam through an anti-torsion pull rod so as to limit the rotation of the fixed ring.
Furthermore, the rotating ring is respectively connected with the rotating shaft in an axial hinged mode through the total distance pull rod, when the rotating ring moves along the output shaft of the brushless motor, the rotating ring drives the rotating shaft to rotate around the output shaft of the brushless motor in an axial hinged mode, a steering engine is arranged between the fixed ring and the cross pipe beam, and the unmanned aerial vehicle drives the rotating ring and the fixed ring to integrally move along the output shaft of the brushless motor through controlling the steering engine so as to achieve adjustment of the propeller pitch.
Further, the fuselage ducted fan at least comprises two layers of blade groups, and the two layers of blade groups are symmetrical about the horizontal plane of the fuselage ducted fan.
Furthermore, the immobile rings between the two layers of blade groups are connected through a linkage pull rod, so that the immobile rings of the two layers of blade groups move synchronously.
Further, the wing tip ducted fan is the same in structure as the fuselage ducted fan.
Further, among the wing tip ducted fan, the one end of cross tubular beams stretches into the wing box of wing and forms the pivot, the pivot passes through the bearing rotation with the wing box of wing and is connected, and the pivot is connected with gear reduction box transmission towards the one end of wing, gear reduction box and the motor that verts are connected, and gear reduction box and the motor that verts all set up in the wing, through the motor drive pivot rotation that verts, in order to drive the wing tip ducted fan verts.
Furthermore, foldable skins are arranged at openings at two ends of the fuselage duct, and the skins can be folded to open or close the fuselage duct through a skin contraction mechanism.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. the fuselage ducted fan is arranged on the fuselage, is mainly used for providing main power for taking off and landing of an aircraft, and provides auxiliary power for the wing tip ducted fan, so that the arrangement is favorable for hovering operation of the aircraft, when the aircraft is in a parallel flight state, the fuselage ducted fan can be turned off, and the power is passed through for the aircraft only through the wing tip ducted fan, so that not only is the energy saved, but also the flight attitude of the aircraft can be adjusted, namely, the operations of forward tilting, backward tilting, left steering, right steering and the like of the aircraft can be realized only by adjusting the tilting angle of the wing tip ducted fan, and the fuselage ducted fan has the characteristics of high flight speed, low noise, simple structure, simple operation and the like, and solves the problems of the traditional eVTOL;
2. the electric vertical take-off and landing unmanned aerial vehicle has a compact structure, is low in manufacturing cost, is favorable for marketization, can compete with the traditional unmanned aerial vehicle on the same platform, and can be used for multiple purposes such as agriculture, investigation, survey and the like;
3. because the invention is provided with two ducted fans, namely the fuselage ducted fan and the wing tip ducted fan, even if one ducted fan fails and stops running, the operation of the aircraft can be maintained by running the other ducted fan, the damage rate of the aircraft is controlled, and the practicability is stronger.
Drawings
FIG. 1 is a schematic diagram of a hovering state of an electric VTOL unmanned aerial vehicle of the present invention;
FIG. 2 is a schematic diagram of the electric VTOL unmanned aerial vehicle of the present invention in a right-turning state;
FIG. 3 is a schematic diagram of the electric VTOL UAV of the present invention in a left-hand steering state;
FIG. 4 is a schematic diagram of the electric VTOL unmanned aerial vehicle of the present invention in a forward leaning state;
FIG. 5 is a schematic view of the electric VTOL UAV of the present invention in a level flight state;
FIG. 6 is a schematic diagram of an electric VTOL unmanned aerial vehicle of the present invention in a sequentially inclined state;
FIG. 7 is a schematic structural view of a ducted fan with a double fuselage according to the present invention;
FIG. 8 is a schematic view of a wingtip ducted fan of the present invention;
fig. 9 is a schematic diagram of logic control of an intelligent flight control system according to the present invention.
The labels in the figure are: the aircraft comprises a main body, a fuselage ducted fan, wings, 31 wing boxes, wing tip ducted fans, a cross-shaped pipe beam 41, a rotating shaft 42, a gear reduction box 43, a tilting motor 44, a V-shaped empennage 5, landing gears 6, an intelligent flight control system 7, upper blades 81, lower blades 82, axial hinges 83, a total distance pull rod 84, a linkage pull rod 85, a brushless motor 86, torsion-proof pull rods 87, a movable ring 88, a fixed ring 89, a steering engine 90 and a hub 91.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
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.
An electric vertical take-off and landing unmanned aerial vehicle comprises a body 1, a body duct fan 2, wings 3, wing tip duct fans 4, a V-shaped empennage 5, landing gears 6 and other main components, wherein as shown in figure 1, the body 1 of a lifting body adopts a wing section design and provides a part of important lifting force for the aerial vehicle during high-speed flight. Along the axis direction of fuselage 1, be provided with two fuselage ducts on the fuselage 1, two fuselage ducts are the symmetry and set up, install fuselage duct fan 2 in the fuselage duct, and it is the vertical column type and arranges inside the fuselage, for the aircraft stage of taking off and land provides main lift, is the load cabin between fuselage duct fan 2, and fuselage duct fan 2 drives through electric power. Further, wings 3 are symmetrically arranged on two sides of the aircraft body 1, the V-shaped tail wings 5 are arranged on the tail portion of the aircraft body 1, the undercarriage 6 is arranged on the lower portion of the aircraft body 1, the wings 3 and the V-shaped tail wings 5 provide lift force and control moment for the aircraft during high-speed flight, a control surface is arranged like a traditional fixed wing aircraft, and deflection of the control surface is controlled through a steering engine during high-speed flight, so that the attitude of the aircraft is controlled.
Furthermore, the wingtip ducted fan 4 is rotatably connected to the wingtip of the wing 3, the wingtip ducted fan 4 can independently tilt forwards or backwards along the wingtip of the wing 3, can provide a small part of lift force for the aircraft in the taking-off and landing stage of the aircraft and provides power when the aircraft flies, the wingtip ducted fan 4 is also driven by electric power, and the driving device of the wingtip ducted fan is arranged inside the wing 3.
Further, the upper opening and the lower opening of the fuselage duct adopt foldable skin design, namely foldable skins for storage are arranged at the openings at the two ends of the fuselage duct, the skins realize opening or closing of the fuselage duct through a skin contraction mechanism (a common contraction mechanism is adopted), for example, a traditional electric telescopic rod mechanism, when the aircraft flies at high speed, the upper skin and the lower skin of the fuselage duct fan 2 are opened to cover the duct, the fuselage is completely and continuously lifted up and down, and the functions of increasing lift and reducing drag are achieved.
Further, the fuselage ducted fan 2 and the wing tip ducted fan 4 are power devices of the aircraft, and power output can be adjusted by changing the rotating speed and changing the pitch of the blades. In order to better realize the electric driving of the fuselage ducted fan 2 of the present invention, fig. 7 shows a double-deck fuselage ducted fan 2 structure, in fig. 7, the upper deck blades 81 and the lower deck blades 82 are symmetrical about the horizontal symmetry plane of the fuselage ducted, and each deck blade is equipped with an independent axial hinge 83, a movable ring 88, a stationary ring 89, a collective tie rod 84, a brushless motor 86, an anti-twist tie rod 87, and is symmetrical about the horizontal symmetry plane of the fuselage ducted. The linkage pull rod 85 is connected with the control mechanism of the two layers of blades and is driven by the steering engine 90. The cross tube beam 41 and the hull of the fuselage 1 combine to form a catenary bearing to support the entire rotor assembly. The center of the cross pipe beam 41 is provided with a motor mounting support, and the upper end surface and the lower end surface of the cross pipe beam are respectively fixed with a brushless motor 86 of the upper layer blade 81 and the lower layer blade 82. The top of the output shaft of the brushless motor 86 is a hub 91, the upper layer blade 81 and the lower layer blade 82 are fixed through an axial hinge 83, the axial hinge 83 can rotate around the axis of the output shaft of the brushless motor 86, the total pitch of the blades, namely the attack angle, changes after the blades rotate, the brushless motor 86 is connected with a power supply through a power transmission line, the power supply is a rechargeable power battery, and can also be a hydrogen fuel battery, and the power supply is generally arranged in the machine body 1 and mainly provides power output for the machine body ducted fan 2 and the wing tip ducted fan 4. The output shaft of the brushless motor 86 is provided with a movable ring 88 and a fixed ring 89, the movable ring 88 and the fixed ring are positioned between the propeller hub 91 and the brushless motor 86, the movable ring 88 is positioned at the inner ring, the movable ring is fixed on the output shaft of the brushless motor 86 through a flat key and rotates along with the output shaft, and the key groove has a certain margin and allows the movable ring 88 to slide up and down relative to the output shaft. The fixed ring 89 is positioned on the outer ring of the movable ring 88, is connected with the movable ring 88 into an assembly through a deep groove ball bearing, realizes rotary connection, can slide upwards or downwards on the output shaft of the brushless motor 86 at the same time, and is connected with the cross pipe beam 41 through the anti-torsion pull rod 87 outside the fixed ring 89 to limit the rotation of the cross pipe beam around the output shaft. Steering engines 90 (2 in total) are arranged between the cross pipe beam 41 and the lower stationary ring 89, and the intelligent flight control system controls the steering engines 90 to drive the movable ring 88 and the stationary ring 89 to integrally slide upwards or downwards. The movable ring 88 is connected with 3 axial hinges 83 through total distance pull rods 84 (totally 3), and the movable ring 88 slides up and down to drive the axial hinges 83 to rotate around the axis of the axial hinges, so that the total distance of 3 blades is changed. The upper stationary ring 89 and the lower stationary ring 89 are connected through linkage pull rods 85 (2 in total), namely the upper moving ring/stationary ring and the lower moving ring/stationary ring follow up, and the total pitch of the 3 upper blades is changed under the driving of the steering engine 90. The steering engine 90 may also be mounted between the upper stationary ring 89 and the cross beam 41.
Further, as for the wing tip ducted fan 4, the wing tip ducted fan 4 may also adopt the same structure as the fuselage ducted fan 2, and other structures and pitch adjustment methods are the same except for the difference in size, and the brushless motor 86 is also provided. However, the wingtip ducted fan 4 needs to realize a forward and backward tilting function, and as an embodiment, as shown in fig. 8, the wingtip ducted fan 4 is integrated on a cross-shaped tubular beam 41, a rotating shaft 42 of the cross-shaped tubular beam 41 is installed in the wing box 31 of the wing 3 through a bearing, one end of the rotating shaft 42 of the cross-shaped tubular beam 41 is connected with a gear reduction box 43, and a tilting motor 44 is connected to an input end of the gear reduction box 43 to drive the wingtip ducted fan 4 to realize forward and backward tilting.
The electric vertical take-off and landing unmanned aerial vehicle innovatively carries out the optimized layout design on the tilting ducted fan and the fixed wings, realizes the vertical take-off and landing function, has the characteristics of high flight speed and low noise, is low in manufacturing cost, and is favorable for marketization.
The electric vertical take-off and landing unmanned aerial vehicle disclosed by the invention has the following corresponding control flight principles:
(1) when the aircraft needs to be suspended, the intelligent flight control system controls the wing tip ducted fan 4 to keep a vertical state, automatically adjusts the rotating speed and the blade pitch of the ducted fan 2 and the wing tip ducted fan 4, and automatically balances and hovers, namely, the aircraft can vertically move up and down by changing the rotating speed and the blade pitch of the fuselage ducted fan 2 and the wing tip ducted fan 4, and the adjustment state is shown in figure 1;
(2) when the aircraft needs to be steered to the right in the hovering posture, after receiving an instruction, the intelligent flight control system controls the right wing tip ducted fan 4 to incline backwards, the left wing tip ducted fan 4 inclines forwards, and the lift force is automatically balanced, so that the right steering of the aircraft is realized, and the adjustment state is shown in fig. 2;
(3) when the aircraft needs to be left steered in a hovering posture, after receiving an instruction, the intelligent flight control system controls the right wing tip ducted fan 4 to be forward inclined, the left wing tip ducted fan 4 is backward inclined, the lift force is automatically balanced, left steering of the aircraft is achieved, and the adjusting state is as shown in fig. 3;
(4) when the aircraft needs to fly forwards, after receiving an instruction, the intelligent flight control system controls the left and right wingtip ducted fans 4 to incline forwards and automatically balance the lift force, so that the forward flight of the aircraft is realized, and the adjustment state is shown in fig. 4;
(5) the lift provided by the wings 3 is correspondingly increased along with the increase of the front flying speed of the aircraft, the fuselage ducted fan 2 gradually reduces the rotating speed until the aircraft does not run any more under the control of the intelligent flight control system (if the design of the folding skin is adopted, the folding skin 6 at the fuselage duct is opened at the moment, the shielding of the fuselage duct is completed), the wing tip ducted fan 4 inclines forwards to be completely horizontal, the power for front flying is provided, the aircraft also controls the control surfaces on the wings 3 and the V-shaped empennage 5 to realize the control of the flying postures of climbing, yawing and the like by the intelligent flight control system, and the adjustment state is shown in figure 5;
(6) when the aircraft needs to be decelerated and landed, after an instruction is received, the intelligent flight control system controls the wing tip ducted fan 4 to slowly change into a backward inclination state, the lift force is automatically balanced, the aircraft is decelerated and landed, and the adjusting state is shown in fig. 6.
Furthermore, the intelligent flight control system related to the invention can adopt a traditional intelligent flight control system, but in order to enable the system to be more matched with the aircraft of the invention, the invention makes some improvements on the basis of the original intelligent flight control system, as shown in fig. 1 and 9, the main body part of the intelligent flight control system 6 is arranged in the aircraft body 1, the main body part takes a flight control computer as a core, and the periphery of the intelligent flight control system comprises a sensor system, an execution mechanism and a power system. The power system is a wing tip ducted fan and a fuselage ducted fan. The sensor system comprises an airspeed head, an Inertial Measurement Unit (IMU), a GPS (global positioning system) and a magnetic compass, and can be used for measuring the vacuum speed of an aircraft platform, the three-axis acceleration and the angular acceleration of an aircraft body, the geographic longitude and latitude, the altitude and the magnetic declination, and transmitting the information to a flight control computer for attitude calculation and flight control. Wherein the Inertial Measurement Unit (IMU) and the GPS receiver have been integrated into the flight control computer chassis, i.e. with reference to existing designs. The power system comprises 3 control ways of an electronic speed regulator, a total distance steering engine and a tilting motor to realize power output combination. The flight control computer can directly send a control signal to the electronic speed regulator of each rotor wing, and the electronic speed regulator controls the rotating speed of the brushless motor through PWM waves so as to control the increase and decrease of the power of the fan. Meanwhile, the flight control computer can control a total pitch motor of each ducted fan to adjust the total pitch of the blades, and further adjust power output. The flight control computer can work out the optimal rotating speed and total distance parameters according to different flight attitudes to realize power efficiency balance, and the algorithm can directly refer to the existing algorithm. Further, in the transition stage of the horizontal flight and the vertical take-off and landing of the aircraft, after the flight control computer receives the control command, the tilt motor is controlled to drive the wing tip ducted fan to tilt through the gear reducer, and the power output adjustment of the horizontal flight and the vertical take-off and landing is realized. The control surface control mechanism comprises an aileron steering engine, a flap steering engine and an empennage steering engine, and the aileron steering engine, the flap steering engine and the empennage steering engine can respond to a control instruction sent by a flight control computer in the flat flight stage to finish the maintenance or adjustment of the posture and the speed of the unmanned aerial vehicle.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. The utility model provides an electronic VTOL unmanned vehicles, includes the fuselage, its characterized in that, along the axis direction of fuselage, the symmetry is provided with a plurality of fuselage ducts on the fuselage, is provided with wing tip duct fan on the wing of fuselage both sides, install fuselage duct fan in the fuselage duct, be the load compartment between the fuselage duct, wing tip duct fan sets up in wing tip department, and rotates with the wing and be connected, fuselage duct fan and wing tip duct fan all drive through electric power, and the rotational speed and the pitch homoenergetic of fuselage duct fan and wing tip duct fan are adjusted to control unmanned vehicles's lift, the wing tip duct fan changes unmanned vehicles's flight gesture through the mode for the wing pivoted.
2. The electric VTOL unmanned aerial vehicle of claim 1, wherein the number of the fuselage ducts is 2, the fuselage duct fan comprises at least one blade set, the blade set comprises a plurality of blades on the same plane, the fixed ends of the blades are connected with an axial hinge, the axial hinge is fixedly connected with a hub, the hub is fixedly connected with an output shaft of a brushless motor, the brushless motor is fixedly connected with a shell of the fuselage through a support beam, an electric input end of the brushless motor is connected with a power supply in the fuselage, and the output shaft of the brushless motor rotates to drive the axial hinge to rotate, thereby driving the blade set to rotate.
3. The unmanned, electric vertical take-off and landing aircraft of claim 2, wherein the support beam is a cross-shaped tubular beam, the brushless motor is fixedly mounted at the center of the cross-shaped tubular beam, and the cross-shaped tubular beam is fixedly connected with the fuselage shell to form a bearing support to support the fuselage ducted fan.
4. The unmanned aerial vehicle for electrical vertical take-off and landing as claimed in claim 3, wherein the brushless motor has an output shaft sleeved with a movable ring and a stationary ring, the movable ring and the stationary ring are located below the hub, the movable ring is fixed to the output shaft of the brushless motor through a flat key and rotates with the output shaft of the brushless motor, a certain margin is left in a key slot of the flat key for mounting the output shaft of the brushless motor to allow the movable ring to slide up and down relative to the output shaft, the stationary ring forms a rolling bearing assembly with the movable ring through a rolling element, and the outer side of the stationary ring is connected with the cross beam through an anti-torsion pull rod to limit the rotation of the stationary ring.
5. The electric VTOL unmanned aerial vehicle of claim 4, wherein the rotating rings are respectively and axially hinged through a collective pitch pull rod, when the rotating rings move along the output shaft of the brushless motor, the rotating rings drive the axial hinges to rotate around the output shaft of the brushless motor, a steering engine is arranged between the fixed rings and the cross pipe beam, and the unmanned aerial vehicle drives the rotating rings and the fixed rings to integrally move along the output shaft of the brushless motor by controlling the steering engine so as to realize the adjustment of the propeller pitch.
6. The unmanned, electric, vertical take-off and landing aircraft of claim 5, wherein the fuselage ducted fan comprises at least two blade sets, the two blade sets being symmetrical about a horizontal plane of the fuselage duct.
7. The unmanned, motorized vertical take-off and landing aircraft as claimed in claim 6, wherein the stationary rings between the two blade sets are connected by a linkage tie rod to move the stationary rings of the two blade sets synchronously.
8. The unmanned, electric vtol aircraft of claim 7, wherein said wing tip ducted fan is structurally identical to said fuselage ducted fan.
9. The unmanned aerial vehicle of claim 8, wherein in the wing tip ducted fan, one end of the cross-shaped tubular beam extends into a wing box of the wing to form a rotating shaft, the rotating shaft is rotatably connected with the wing box of the wing through a bearing, one end of the rotating shaft facing the wing is in transmission connection with a gear reduction box, the gear reduction box is connected with a tilting motor, the gear reduction box and the tilting motor are both arranged in the wing, and the rotating shaft is driven to rotate through the tilting motor to drive the wing tip ducted fan to tilt.
10. The unmanned, motorized vertical take-off and landing aircraft according to any one of claims 1 to 9, wherein foldable skins are provided at the openings at both ends of the fuselage duct, and the skins are configured to open or close the fuselage duct by a skin retraction mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202111542722.6A CN114180046A (en) | 2021-12-16 | 2021-12-16 | Electric vertical take-off and landing unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111542722.6A CN114180046A (en) | 2021-12-16 | 2021-12-16 | Electric vertical take-off and landing unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114771827A (en) * | 2022-05-27 | 2022-07-22 | 云翼航空科技(深圳)有限公司 | Aircraft capable of taking off and landing vertically and control method thereof |
Citations (7)
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| CN103448910A (en) * | 2013-08-31 | 2013-12-18 | 西北工业大学 | Aircraft capable of vertically taking off and landing at high speed |
| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
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| CN114771827A (en) * | 2022-05-27 | 2022-07-22 | 云翼航空科技(深圳)有限公司 | Aircraft capable of taking off and landing vertically and control method thereof |
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