CN109279007B - Composite driving rotor wing fixed wing unmanned aerial vehicle - Google Patents
Composite driving rotor wing fixed wing unmanned aerial vehicle Download PDFInfo
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- CN109279007B CN109279007B CN201811390295.2A CN201811390295A CN109279007B CN 109279007 B CN109279007 B CN 109279007B CN 201811390295 A CN201811390295 A CN 201811390295A CN 109279007 B CN109279007 B CN 109279007B
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- 239000002131 composite material Substances 0.000 title claims abstract description 10
- 238000000034 method Methods 0.000 claims abstract description 21
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 15
- 239000011152 fibreglass Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 230000007704 transition Effects 0.000 abstract description 10
- 150000001875 compounds Chemical class 0.000 description 8
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- 240000007182 Ochroma pyramidale Species 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
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- 239000003365 glass fiber Substances 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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Abstract
The invention discloses a composite-driving rotor wing fixed wing unmanned aerial vehicle, which adopts full-electric driving vertical take-off and landing and front flight cruising, and utilizes the layout of a composite inverted V-shaped tail wing and an equal chord length rectangular four straight wing surface in an axisymmetric manner; adopt rotor subassembly to realize taking off and land perpendicularly, unmanned aerial vehicle takes off and land perpendicularly and is not restricted by the place, and it is little to hang down the height loss that changes flat transition mode, and stability is high. The forward flight cruising is realized by adopting the propeller and the driving motor, and the forward flight cruising speed of the unmanned aerial vehicle is high and the continuous time is long. The pneumatic efficiency of the tail wing of the unmanned aerial vehicle in the flight process can be ensured by utilizing the pneumatic principle that the composite inverted V-shaped tail wing accords with the unmanned aerial vehicle; the unmanned aerial vehicle adopts rectangular straight airfoil surfaces and rotor arm structural layout to provide larger lifting force, so that the cruising efficiency and the front flying speed of the unmanned aerial vehicle can be greatly improved when the unmanned aerial vehicle flies forwards to cruise, the integral structural rigidity of the unmanned aerial vehicle is ensured, and the structural stability in the flight process of the unmanned aerial vehicle and the flight safety of the unmanned aerial vehicle are ensured.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a compound-driven rotor wing fixed wing unmanned aerial vehicle.
Background
Aircraft design professionals and researchers have been trying to design an aircraft that can be short-range or has vertical take-off and landing and forward-flight cruise capabilities. At present, in practical application, an aircraft which adopts a rotor wing combination to realize vertical take-off and landing is mature, unmanned aircraft in many fields shows remarkable performance, and gradually steps into a stage of people's life. The multi-rotor unmanned aerial vehicle has the vertical take-off and landing performance, so that the multi-rotor unmanned aerial vehicle has important roles in the technical fields of aerial photography and aerial survey, has a simple structure, lighter weight, strong maneuverability and high reliability, but the multi-rotor unmanned aerial vehicle is smaller in size, has no fixed lifting surface, has low cruising efficiency, is not fast in flying speed, and has certain limitation on flying distance and application range. The fixed wing unmanned aerial vehicle has the forward flight cruising performance, plays an important role in various fields of forest fire prevention and power pipe network inspection, and has the advantages of high cruising efficiency, high flying speed and high flexibility, but the fixed wing unmanned aerial vehicle does not have the vertical take-off and landing performance, and the application range of the fixed wing aircraft is limited by the requirements on a runway and a running distance.
Chinese patent CN205770149 discloses a "multi-configuration fixed-wing rotor hybrid unmanned aerial vehicle", comprising a rotor assembly, a fixed-wing system and an equipment bay, in which a flight controller, sensors and a power supply are placed in the bay of the equipment bay. The unmanned aerial vehicle is formed by combining a fixed wing body and four rotary wings, and has the performances of vertical take-off and landing and front flying cruising. The unmanned aerial vehicle is characterized in that the unmanned aerial vehicle can be switched among three modes of a rotor unmanned aerial vehicle, a fixed wing unmanned aerial vehicle and a hybrid unmanned aerial vehicle according to requirements, the application range and the application range are wider, but the unmanned aerial vehicle has the structure that a rotor assembly is directly fixedly connected on a machine body through a connecting rod, the structural strength is weaker, the lifting force is only provided by double wings, and the cruising efficiency is low.
Patent CN206141829 discloses a "fixed-wing multi-rotor composite aircraft" comprising a main body skeleton, a tilting engine, an aircraft fuselage, a rectangular wing and an aircraft fuselage sweep angle. The aircraft has vertical take-off and landing and front flight cruising performances, realizes conversion between the vertical take-off and landing and front flight cruising of the unmanned aerial vehicle by adopting a rotor engine tilting mode, and is characterized by reducing the weight of the aircraft during front flight cruising, improving the front flight cruising efficiency, and being relatively complex in method for tilting the forward engine to carry out transition between the vertical take-off and landing and the front flight cruising and relatively high in cost.
Disclosure of Invention
In order to avoid the defects in the prior art, the invention provides a compound-driven rotor wing fixed wing unmanned aerial vehicle, which adopts full-electric vertical lifting, and the vertical lifting is not limited by a use place; the composite inverted V-shaped tail wing layout ensures the efficiency of the control surface of the unmanned aerial vehicle in the vertical leveling and transition mode and the overall stability of the unmanned aerial vehicle; the four-straight-wing-surface layout is adopted, so that the decline of the flying height in the unmanned aerial vehicle vertical-lifting leveling flying transition mode is reduced, the unmanned aerial vehicle is enabled to be safe and reliable, the four-straight-wing-surface layout provides larger lifting force when the unmanned aerial vehicle flies forward to cruise, and the forward flying cruise efficiency and the flying speed of the unmanned aerial vehicle are improved.
The invention solves the technical problems by adopting the technical scheme that the novel aircraft comprises a first rotor wing assembly, a second rotor wing assembly, a third rotor wing assembly, a fourth rotor wing assembly, a first propeller, a second propeller, an aircraft body, a flight control system, a battery, a first wing, a second wing, a third wing, a fourth wing, a nose landing gear, a rear landing gear, a first rotor wing arm, a second rotor wing arm, an aileron, a driving motor, a first tail wing and a second tail wing, and is characterized in that the aircraft body is formed by adopting glass fiber reinforced plastics, the cross sections of the head part and the tail part of the aircraft body are elliptic, and the two sides of the aircraft body are respectively provided with the first wing, the third wing, the second wing and the fourth wing which are respectively arranged in an axisymmetric manner; the first wing, the second wing, the third wing and the fourth wing are rectangular straight wing surface structures with equal chord lengths, the aspect ratio is 6-8, and the dihedral angle of the wings is 0-10 degrees; one end of the first rotor arm is fixedly connected with a first wing tip part, the other end of the first rotor arm is fixedly connected with a second wing tip part, one end of the second rotor arm is fixedly connected with a third wing tip part, and the other end of the second rotor arm is fixedly connected with a fourth wing tip part; the driving motor is fixed at the middle parts of the front edges of the first wing and the third wing, the 2/3 positions of the rear edges of the second wing and the fourth wing are respectively provided with ailerons, and the two ailerons are respectively hinged with the second wing and the fourth wing; the first propeller and the second propeller are respectively and fixedly connected to the front end of the driving motor, the first propeller and the second propeller are identical in structure, and the first propeller and the second propeller are opposite in rotation in the working process;
The first rotor wing assembly, the second rotor wing assembly, the third rotor wing assembly and the fourth rotor wing assembly are parts with the same structure, wherein the rotor wings are positioned on the upper part of the motor, a plurality of rotor wings are installed in a matched mode with the motors with the same quantity, the rotor wings and the motors are symmetrically fixed on the first rotor wing arm and the second rotor wing arm respectively, the first rotor wing assembly, the second rotor wing assembly, the third rotor wing assembly and the fourth rotor wing assembly are all positioned on the same plane, the rotor wings of the first rotor wing assembly and the fourth rotor wing assembly rotate clockwise when in operation, and the rotor wings of the second rotor wing assembly and the third rotor wing assembly rotate anticlockwise when in operation;
the first tail wing and the second tail wing form a combined inverted V-shaped tail wing, and the lower dihedral angle of the first tail wing and the second tail wing is 30-60 degrees;
The nose landing gear is located at 1/4 of the bottom of the machine body, the rear landing gear is located at 2/3 of the bottom of the machine body, the height of the nose landing gear and the rear landing gear is greater than that of the V-shaped tail wing, and the V-shaped tail wing cannot touch the ground when the unmanned aerial vehicle is placed on the ground or vertically lifted.
The battery and the flight control system are respectively positioned at the middle part in the machine body, the battery is 1-2 6s batteries, the installation position of the battery is adjustable, and the battery is used for providing power for the rotor motor and the propeller driving motor; the flight control system is used for guaranteeing the control and stability of the unmanned aerial vehicle in the flight process.
Advantageous effects
The rotor wing fixed wing unmanned aerial vehicle with the compound drive adopts full-electric vertical take-off and landing and front flight cruising, and utilizes the compound inverted V-shaped tail wing and straight wing surface structure, so that the vertical take-off and landing is not limited by places, the height loss of a vertical take-off and leveling transition mode is less, the stability is high, the front flight cruising efficiency of the unmanned aerial vehicle is high, the speed is high, and the flight time is long; the unmanned aerial vehicle adopts the four-straight wing surface layout, the provided lifting force is large, and the cruising efficiency and the forward flying speed of the unmanned aerial vehicle can be greatly improved when the unmanned aerial vehicle flies forward to cruise; in the unmanned aerial vehicle hanging-up leveling transition mode, the four straight airfoil surface layout can ensure that the flight height of the unmanned aerial vehicle cannot be reduced, and further ensure the flight safety of the unmanned aerial vehicle.
According to the rotor wing fixed wing unmanned aerial vehicle with compound driving, the first rotor wing arm and the second rotor wing arm are respectively and symmetrically fixed to the rotor wing components, and the two rotor wing arms are respectively and fixedly connected with the four wings. The adoption combined type inverted V-shaped fin makes unmanned aerial vehicle's pneumatic efficiency high at flight in-process fin, because unmanned aerial vehicle has great resistance component at its upper surface when flying, can disturb the air current that flows to unmanned aerial vehicle tail wing, and then reduces unmanned aerial vehicle flight in-process fin's pneumatic efficiency, causes the lower problem of fin operability, and the operability of unmanned aerial vehicle fin can be guaranteed to combined type inverted V-shaped fin, and accords with rotor wing fixed wing unmanned aerial vehicle's pneumatic principle.
Drawings
The invention relates to a composite driving rotor wing fixed wing unmanned aerial vehicle, which is further described in detail below with reference to the accompanying drawings and the implementation modes.
Fig. 1 is an isometric view of a composite-drive rotor wing fixed wing unmanned aerial vehicle of the present invention.
Fig. 2 is a front view of the composite-drive rotor wing fixed wing unmanned aerial vehicle of the present invention.
Fig. 3 is a top view of the composite-driven rotor wing fixed wing unmanned aerial vehicle of the present invention.
Fig. 4 is a side view of the composite-drive rotor wing fixed wing unmanned aerial vehicle of the present invention.
In the figure:
1. First rotor assembly 2, second rotor assembly 3, third rotor assembly 4, fourth rotor assembly 5, first rotor 6, second rotor 7, fuselage 8, flight control system 9, battery 10, first wing 11, second wing 12, third wing 13, fourth wing 14, nose landing gear 15, rear landing gear 16, first rotor arm 17, second rotor arm 18, aileron 19, drive motor 20, first tail 21, second tail
Detailed Description
The embodiment is a compound driven rotor wing fixed wing unmanned aerial vehicle.
Referring to fig. 1 to 4, the rotor wing fixed wing unmanned aerial vehicle with compound driving in this embodiment adopts electric vertical take-off and landing and forward flight cruising, and utilizes four-wing surface layout and compound inverted V-shaped tail wing structure, so as to ensure that the unmanned aerial vehicle has vertical take-off and landing and forward flight cruising performances, ensure the safety and stability of the unmanned aerial vehicle in a vertical take-off and leveling flight transition mode, and improve forward flight cruising efficiency and flight speed of the unmanned aerial vehicle.
In this embodiment, first rotor subassembly 1, second rotor subassembly 2, third rotor subassembly 3 and fourth rotor subassembly 4 all include the same rotor and motor, and the rotor is used for unmanned aerial vehicle's perpendicular take off and land process, does not take place to rotate when unmanned aerial vehicle flies at the front and cruises. The first rotor assembly 1, the second rotor assembly 2 are fixedly connected with the first rotor arm 16 respectively, the third rotor assembly 3 and the fourth rotor assembly 4 are fixedly connected with the second rotor arm 17 respectively, and the interval between the two rotor assemblies can ensure that the rotors can not touch each other when rotating. The two ends of the first rotor arm 16 are respectively fixedly connected with the wingtip of the first wing 10 and the wingtip of the second wing 11, and the two ends of the second rotor arm 17 are respectively fixedly connected with the wingtip of the third wing 12 and the wingtip of the fourth wing 13, so that the tensile force generated by the rotor can be transmitted to the fuselage 7. The rotors of the first rotor wing assembly 1 and the fourth rotor wing assembly 4 rotate clockwise, and the rotors of the second rotor wing assembly 2 and the third rotor wing assembly 3 rotate anticlockwise, so that the moment generated in the rotation process of the rotors can be balanced. The wing roots of the first wing 10, the second wing 11, the third wing 12 and the fourth wing 13 are fixedly connected with the unmanned aerial vehicle body 7 so as to ensure that the lift force generated by the wing surfaces is transmitted to the body 7. The first wing 10, the second wing 11, the third wing 12, the fourth wing 13 and the fuselage 7 are made of balsawood or glass fiber reinforced plastic materials with better strength and rigidity; in this example, the first wing 10, the second wing 11, the third wing 12, the fourth wing 13 and the fuselage 7 are made of glass fibre reinforced plastics. The first wing 10, the second wing 11, the third wing 12 and the fourth wing 13 are all rectangular straight wing structures with equal chord lengths, the aspect ratio is 7, and the dihedral angle is 5 degrees. The cross section of the head of the unmanned aerial vehicle is elliptical, the cross section area is larger, the cross section of the tail of the unmanned aerial vehicle 7 is elliptical, the cross section area is smaller, the whole unmanned aerial vehicle 7 is an elongated body, and the cross section area is increased and then reduced; the middle part of the machine body 7 is used for installing a battery 9 and a flight control system 8, and the tail part of the machine body 7 is upturned and fixedly connected with the first tail wing 20 and the second tail wing 21. The first propeller 5 and the second propeller 6 are positioned at the front end of the driving motor 19, the driving motor 19 drives the propellers to rotate, and the rotation directions of the first propeller 5 and the second propeller 6 are opposite in the working process; the first propeller 5 rotates clockwise in this example and the second propeller 6 rotates anticlockwise. The first propeller 5 and the second propeller 6 are respectively arranged at the front edge of the first wing 10 and the third wing 12 and positioned at the 1/2 position of the wings; ailerons 18 are mounted at the rear 2/3 positions of the second wing 11 and the fourth wing 13, and are hinged with the second wing and the fourth wing respectively so as to operate the unmanned aerial vehicle. The largest part of the cross section area of the middle part of the machine body 7 is provided with a large opening, and a battery 9 and a flight control system 8 are arranged inside the machine body 7 so as to ensure the supply of an unmanned aerial vehicle power system and assist the operation of the unmanned aerial vehicle in the flight process; in this example the large opening in the fuselage of the unmanned aerial vehicle is located at 1/2 of the fuselage. The batteries 9 are 1-2 6s batteries; the example adopts 1 piece 6s battery, and the electric wire is in the same place battery 9 and rotor motor and driving motor 19 through the lightening hole of first wing 10, second wing 11, third wing 12 and fourth wing 13, accomplishes unmanned aerial vehicle power system's matching. The flight control system 8 comprises a flight control board for assisting the control of the unmanned aerial vehicle and recording flight data of the unmanned aerial vehicle. The front landing gear 14 is fixedly connected to 1/4 of the fuselage, and the rear landing gear 15 is fixedly connected to 2/3 of the fuselage, so that the unmanned aerial vehicle can be used when being placed on the ground or lifted vertically; the front landing gear 14 and the rear landing gear 15 are identical in height and are larger than the first tail wing 20 and the second tail wing 21 to form a combined inverted-V-shaped tail wing, so that the combined inverted-V-shaped tail wing cannot touch the ground when the unmanned aerial vehicle is placed on the ground or takes off; the transverse course stability and the operability of the unmanned aerial vehicle are ensured; the lower dihedral angle of the first tail wing 20 and the second tail wing is 30-60 degrees; the dihedral angles of the first tail 20 and the second tail 21 in this example are 45 degrees.
The flight modes of the unmanned aerial vehicle in the embodiment are a vertical take-off and landing mode, a vertical take-off and leveling flight transition mode and a front flight cruise mode.
In the vertical take-off and landing mode, in the vertical take-off process of the unmanned aerial vehicle, the first rotor wing assembly 1, the second rotor wing assembly 2, the third rotor wing assembly 3 and the fourth rotor wing assembly 4 rotate under the drive of a motor to provide upward lift force for the vertical take-off and landing of the unmanned aerial vehicle; the first propeller 5, the second propeller 6 and the driving motor 19 do not rotate in the vertical take-off process of the unmanned aerial vehicle; the first tail wing 20, the second tail wing 21 and the aileron 18 ensure the lateral and longitudinal stability of the unmanned aerial vehicle during the vertical take-off of the unmanned aerial vehicle. In the vertical take-off process, the first rotor wing assembly 1, the second rotor wing assembly 2, the third rotor wing assembly 3 and the fourth rotor wing assembly 4 are controlled through the flight control system 8 to control the unmanned aerial vehicle, so that the unmanned aerial vehicle can take off normally and vertically. In the vertical take-off process of the unmanned aerial vehicle, the rotary wing rotating speeds of the first rotary wing assembly 1, the second rotary wing assembly 2, the third rotary wing assembly 3 and the fourth rotary wing assembly 4 are gradually increased until the rotary wing rotating speeds are stable, the flying height of the unmanned aerial vehicle is gradually increased, and when the flying height of the unmanned aerial vehicle reaches more than 100m, the vertical take-off process of the unmanned aerial vehicle is completed. The vertical landing of unmanned aerial vehicle is opposite with unmanned aerial vehicle's vertical take-off process, first rotor subassembly 1, second rotor subassembly 2, the rotor rotational speed of third rotor subassembly 3 and fourth rotor subassembly 4 is by steadily reducing gradually, when unmanned aerial vehicle drops on ground through nose landing gear 14 and back landing gear 15, first rotor subassembly 1, second rotor subassembly 2, the rotor rotational speed of third rotor subassembly 3 and fourth rotor subassembly 4 reduces to zero, unmanned aerial vehicle drops to ground smoothly, its vertical landing process ends.
In the process of converting the vertical take-off and landing mode into the front flight cruising mode, the unmanned aerial vehicle needs to pass through a dynamic transition stage of the vertical take-off and landing flight, and the flight mode of the unmanned aerial vehicle in the stage is called as a vertical take-off and landing flight transition mode of the unmanned aerial vehicle; in the mode, the flying height of the unmanned aerial vehicle exceeds 100m, the front flying speed of the unmanned aerial vehicle reaches more than 15m/s, and the mode is finished; in this mode, the rotor speeds of the first rotor assembly 1, the second rotor assembly 2, the third rotor assembly 3 and the fourth rotor assembly 4 are gradually reduced until zero. The rotational speeds of the first propeller 5, the second propeller 6 and the driving motor 19 are gradually increased until they stabilize. The first rotor wing component 1, the second rotor wing component 2, the third rotor wing component 3 and the fourth rotor wing component 4 are still controlled by a flight control system in the early stage of the flight mode, and when the current flight speed reaches more than 5m/s, unmanned aerial vehicle control is performed by a first tail wing 20, a second tail wing 21, an aileron 18 and a flight control system 8; the first wing 10, the second wing 11, the third wing 12 and the fourth wing 13 generate a large lift in this flight mode, in which the flying height of the unmanned aerial vehicle is not greatly reduced.
A front flight cruising mode, wherein the rotating speeds of the first rotor wing assembly 1, the second rotor wing assembly 2, the third rotor wing assembly 3 and the fourth rotor wing assembly 4 of the unmanned plane are zero; the first propeller 5, the second propeller 6 and the driving motor 19 have stable rotation speeds and are used for providing pulling force for the forward flight of the unmanned aerial vehicle; the first tail wing 20, the second tail wing 21, the aileron 18 and the flight control system 8 are utilized to control the unmanned aerial vehicle; the first wing 10, the second wing 11, the third wing 12 and the fourth wing 13 generate larger lift force so as to overcome the gravity of the unmanned aerial vehicle and ensure the stable cruising of the unmanned aerial vehicle.
Claims (2)
1. The composite-driven rotor wing fixed wing unmanned aerial vehicle comprises a first rotor wing assembly, a second rotor wing assembly, a third rotor wing assembly, a fourth rotor wing assembly, a first propeller, a second propeller, a machine body, a flight control system, a battery, a first wing, a second wing, a third wing, a fourth wing, a nose landing gear, a rear landing gear, a first rotor wing arm, a second rotor wing arm, an aileron, a driving motor, a first tail wing and a second tail wing, and is characterized in that the machine body is formed by glass fiber reinforced plastic, the cross sections of the head part and the tail part of the machine body are elliptical, the two sides of the machine body are respectively provided with the first wing, the third wing, the second wing and the fourth wing, and the first wing, the third wing and the second wing are respectively and symmetrically arranged by the machine body; the first wing, the second wing, the third wing and the fourth wing are rectangular straight wing surface structures with equal chord lengths, the aspect ratio is 6-8, and the dihedral angle of the wings is 0-10 degrees; one end of the first rotor arm is fixedly connected with a first wing tip part, the other end of the first rotor arm is fixedly connected with a second wing tip part, one end of the second rotor arm is fixedly connected with a third wing tip part, and the other end of the second rotor arm is fixedly connected with a fourth wing tip part; the driving motor is fixed at the middle parts of the front edges of the first wing and the third wing, the 2/3 positions of the rear edges of the second wing and the fourth wing are respectively provided with ailerons, and the two ailerons are respectively hinged with the second wing and the fourth wing; the first propeller and the second propeller are respectively and fixedly connected to the front end of the driving motor, the first propeller and the second propeller are identical in structure, and the first propeller and the second propeller are opposite in rotation in the working process;
The first rotor wing assembly, the second rotor wing assembly, the third rotor wing assembly and the fourth rotor wing assembly are parts with the same structure, wherein the rotor wings are positioned on the upper part of the motor, a plurality of rotor wings are installed in a matched mode with the motors with the same quantity, the rotor wings and the motors are symmetrically fixed on the first rotor wing arm and the second rotor wing arm respectively, the first rotor wing assembly, the second rotor wing assembly, the third rotor wing assembly and the fourth rotor wing assembly are all positioned on the same plane, the rotor wings of the first rotor wing assembly and the fourth rotor wing assembly rotate clockwise when in operation, and the rotor wings of the second rotor wing assembly and the third rotor wing assembly rotate anticlockwise when in operation;
the first tail wing and the second tail wing form a combined inverted V-shaped tail wing, and the lower dihedral angle of the first tail wing and the second tail wing is 30-60 degrees;
The nose landing gear is located at 1/4 of the bottom of the machine body, the rear landing gear is located at 2/3 of the bottom of the machine body, the height of the nose landing gear and the rear landing gear is greater than that of the V-shaped tail wing, and the V-shaped tail wing cannot touch the ground when the unmanned aerial vehicle is placed on the ground or vertically lifted.
2. The composite-driven rotor wing fixed wing unmanned aerial vehicle of claim 1, wherein the battery and the flight control system are respectively positioned at the middle part in the body, the battery is 1-2 6s batteries, the installation position of the battery is adjustable, and the battery is used for providing power for a rotor motor and a propeller driving motor; the flight control system is used for guaranteeing the control and stability of the unmanned aerial vehicle in the flight process.
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| CN201811390295.2A CN109279007B (en) | 2018-11-21 | 2018-11-21 | Composite driving rotor wing fixed wing unmanned aerial vehicle |
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| CN201811390295.2A CN109279007B (en) | 2018-11-21 | 2018-11-21 | Composite driving rotor wing fixed wing unmanned aerial vehicle |
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| CN209176908U (en) * | 2018-11-21 | 2019-07-30 | 西北工业大学 | A kind of rotor fixed-wing unmanned plane of composite drive |
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| CN105314107B (en) * | 2014-06-24 | 2019-03-05 | 王泽民 | A method of realizing the vertical landing of existing unmanned aerial vehicle |
| CN106741820A (en) * | 2016-12-20 | 2017-05-31 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned vehicle |
| CN106927036A (en) * | 2017-02-28 | 2017-07-07 | 中航维拓（天津）科技有限公司 | A kind of dynamic four rotor wing unmanned aerial vehicles at a high speed of folding combined type oil |
| US10577091B2 (en) * | 2017-04-24 | 2020-03-03 | Bcg Digital Ventures Gmbh | Vertical take-off and landing aircraft |
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| CN209176908U (en) * | 2018-11-21 | 2019-07-30 | 西北工业大学 | A kind of rotor fixed-wing unmanned plane of composite drive |
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