CN113682471A - Rotor solar energy unmanned aerial vehicle verts - Google Patents

Rotor solar energy unmanned aerial vehicle verts Download PDF

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Publication number
CN113682471A
CN113682471A CN202111244275.6A CN202111244275A CN113682471A CN 113682471 A CN113682471 A CN 113682471A CN 202111244275 A CN202111244275 A CN 202111244275A CN 113682471 A CN113682471 A CN 113682471A
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CN
China
Prior art keywords
wing
solar
drone
aerial vehicle
unmanned aerial
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Pending
Application number
CN202111244275.6A
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Chinese (zh)
Inventor
张凯
佟阳
张练
郭有光
仪志胜
李新军
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China Academy of Aerospace Aerodynamics CAAA
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China Academy of Aerospace Aerodynamics CAAA
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Filing date
Publication date
Application filed by China Academy of Aerospace Aerodynamics CAAA filed Critical China Academy of Aerospace Aerodynamics CAAA
Priority to CN202111244275.6A priority Critical patent/CN113682471A/en
Publication of CN113682471A publication Critical patent/CN113682471A/en
Pending legal-status Critical Current

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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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L8/00—Electric propulsion with power supply from forces of nature, e.g. sun or wind
    • B60L8/003—Converting light into electric energy, e.g. by using photo-voltaic systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • 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
    • 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
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
    • H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2200/00—Type of vehicles
    • B60L2200/10—Air crafts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Power Engineering (AREA)
  • Transportation (AREA)
  • Toys (AREA)

Abstract

The invention discloses a tilt rotor solar unmanned aerial vehicle, which comprises: the wing is of a flying wing structure, and a flexible conformal solar cell array is laid on the upper surface of the wing; three propellers, wherein one pair of propellers is symmetrically arranged at the front edge of the wing, and the other propeller is arranged at the rear edge of the wing and is positioned on the symmetry axis of the wing; the three mechanism that verts, every it corresponds with one to vert the mechanism the screw is connected, it is used for the drive to vert the mechanism the screw for the plane at wing place verts. According to the invention, the propeller is tilted through the tilting mechanism, so that the solar unmanned aerial vehicle can realize vertical take-off and landing, hovering, side flying and back flying of the gyroplane, and can also realize long-distance long-endurance flying of a fixed-wing aircraft.

Description

Rotor solar energy unmanned aerial vehicle verts
Technical Field
The invention belongs to the field of aeronautical engineering, and particularly relates to a tilt rotor solar unmanned aerial vehicle.
Background
The solar unmanned aerial vehicle has attracted extensive attention and gained rapid development in recent years because of its advantages such as long cruising time, high flying height, wide coverage area, use cost low. Present solar energy unmanned aerial vehicle at home and abroad is mostly fixed wing unmanned aerial vehicle to adopt the take-off and landing mode of horizontal rollerball, this kind of solar energy unmanned aerial vehicle has following not enoughly: (1) the use is limited depending on the taking off and landing of the airport runway; (2) a wider runway is usually required in the take-off and landing stage, and higher requirements are provided for the wind speed and the wind direction at that time; (3) specific actions such as autonomous hovering and flying-off cannot be realized in the air.
Therefore, the tilting rotor solar unmanned aerial vehicle can realize vertical take-off and landing, hovering, side flying and back flying of the gyroplane and can also realize long-distance long-endurance flying of a fixed-wing aircraft through the tilting propeller mechanism.
Disclosure of Invention
The invention aims to provide a tilt rotor solar unmanned aerial vehicle, which can realize vertical take-off and landing, hovering, side flying and rear flying of a gyroplane and can also realize long-distance long-endurance flying of a fixed-wing aircraft.
In order to achieve the above object, the present invention provides a tilt rotor solar unmanned aerial vehicle, comprising:
the wing is of a flying wing structure, and a flexible conformal solar cell array is laid on the upper surface of the wing;
three propellers, wherein one pair of propellers is symmetrically arranged at the front edge of the wing, and the other propeller is arranged at the rear edge of the wing and is positioned on the symmetry axis of the wing;
the three mechanism that verts, every it corresponds with one to vert the mechanism the propeller is connected, it is used for the drive to vert the mechanism the propeller for the plane at wing place verts.
As an alternative, a storage battery is installed inside the unmanned aerial vehicle, and the solar cell array provides electric energy for the storage battery; and the unmanned aerial vehicle is provided with a power motor for driving the propeller to rotate, and the power motor is connected with the storage battery.
As an alternative, the tilting mechanism is provided inside the wing, the tilting mechanism comprising: mount, telescopic machanism and link assembly, the mount is fixed on the unmanned aerial vehicle, the root fixed connection of screw in link assembly, link assembly respectively with the mount reaches telescopic machanism's flexible end is articulated, telescopic machanism is used for the drive link assembly rotates, so that the screw takes place to vert.
Alternatively, the wing has an aspect ratio greater than 15.
As an alternative, the drone includes a vertical fin disposed on an upper surface of a wing tip of the wing, and the wing and the vertical fin are perpendicular to each other.
As an alternative, the unmanned aerial vehicle includes a landing gear, the landing gear is a three-point type, two fulcrums of the landing gear are arranged on the lower surface of the wing tip of the wing and opposite to the vertical tail, and the other fulcrum is arranged on the lower surface of the unmanned aerial vehicle and located on the symmetry axis of the wing.
Alternatively, the drone comprises a pair of ailerons symmetrically disposed at the trailing edge of the wing.
Alternatively, the drone comprises a pair of rudders, the rudders being disposed at the trailing edge of the vertical tail.
Alternatively, the number of blades per propeller is two.
As an alternative, the tilting mechanism comprises a controller for monitoring and controlling the tilting angle of the propeller.
The invention has the beneficial effects that:
(1) the tilt rotor solar unmanned aerial vehicle can take off and land vertically, does not depend on an airport runway, is more flexible to use, and can not only realize vertical take off and land, hovering, side flying and back flying of a rotorcraft, but also realize long-distance long-endurance flying of a fixed-wing aircraft.
(2) The tilt rotor solar unmanned aerial vehicle adopts the layout of the flying wings with large aspect ratio, so that on one hand, the lift-drag ratio is high, and the performance is good when the tilt rotor solar unmanned aerial vehicle is used as a fixed wing for flying; on the other hand compact structure does benefit to the switching of arranging and rotor and fixed wing flight mode of tilting propeller.
(3) Three sets of tilting propellers of the tilting rotor solar unmanned aerial vehicle are respectively arranged at the front edge and the rear edge of the wing, so that the whole aircraft is uniformly stressed and has good stability when the tilting rotor solar unmanned aerial vehicle is used as a gyroplane to fly.
(4) Two sets of tilting propellers of the front edge of the tilting rotor solar unmanned aerial vehicle are arranged at the middle position in the wingspan direction of the unmanned aerial vehicle, and the requirement on the rigidity of a wing structure is low.
The present invention has other features and advantages which will be apparent from or are set forth in detail in the accompanying drawings and the following detailed description, which are incorporated herein, and which together serve to explain certain principles of the invention.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings.
Fig. 1 shows an effect diagram of a tilt rotor solar drone according to an embodiment of the present invention when flying in a rotor state (with a propeller in a turn-up state).
Fig. 2 shows an effect diagram of a tilt rotor solar drone according to an embodiment of the invention when flying in a fixed-wing state (with the propellers in an unruptured state).
Fig. 3 shows a top view of a tiltrotor solar drone according to an embodiment of the present invention.
Fig. 4 shows a front view of a tiltrotor solar drone according to an embodiment of the invention.
Fig. 5 illustrates a side view of a tiltrotor solar drone according to an embodiment of the present invention.
Reference numerals
1-an airfoil; 2-a solar cell array; 3-a storage battery; 4-airborne equipment; 5, a propeller; 6-a power motor; 7-a tilting mechanism; 8-vertical tails; 9-ailerons; 10-a rudder; 11-undercarriage.
Detailed Description
The present invention will be described in more detail below. While the present invention provides preferred embodiments, it should be understood that the present invention may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; may be mechanically coupled, may be directly coupled, or may be indirectly coupled through an intermediary. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
An embodiment of the present invention provides a tilt rotor solar unmanned aerial vehicle, and fig. 1 shows an effect diagram of a tilt rotor solar unmanned aerial vehicle according to an embodiment of the present invention when the tilt rotor solar unmanned aerial vehicle is in a rotor state (a propeller is in a turn-up state) and flies. Fig. 2 shows an effect diagram of a tilt rotor solar drone according to an embodiment of the invention when flying in a fixed-wing state (with the propellers in an unruptured state). Fig. 3 shows a top view of a tiltrotor solar drone according to an embodiment of the present invention. Fig. 4 shows a front view of a tiltrotor solar drone according to an embodiment of the invention. Fig. 5 illustrates a side view of a tiltrotor solar drone according to an embodiment of the present invention. Referring to fig. 1-5, the tilt rotor solar drone comprises:
the aircraft wing comprises a wing 1, wherein the wing is in a flying wing configuration, and a flexible conformal solar cell array 2 is laid on the upper surface of the wing 1;
three propellers 5, wherein one pair of propellers 5 is symmetrically arranged at the front edge of the wing 1, and the other propeller 5 is arranged at the rear edge of the wing 1 and is positioned on the symmetry axis of the wing 1;
and three tilting mechanisms 7, wherein each tilting mechanism 7 is correspondingly connected with one propeller 5, and the tilting mechanisms 7 are used for driving the propeller 5 to tilt relative to the plane where the wing 1 is located.
Referring to fig. 1 to 3, the wings of the drone of the present embodiment adopt a flying-wing configuration (flying-wing), that is, a flying-wing layout form in an aerodynamic layout of an airplane. Without a horizontal tail and a definite fuselage, the fuselage and the wings are a fusion. Passengers, equipment and effective loads are all arranged in the wings, and airborne equipment 4 such as navigation, flight control, measurement and control can be further installed in the wings. The flying wing layout is adopted to serve as a main lifting surface of the unmanned aerial vehicle. In one particular example, the wing 1 is of a high aspect ratio aerodynamic configuration, such as an aspect ratio greater than 15. The high lift-drag ratio is high on one hand by adopting the layout of the high-aspect-ratio flying wing, and the performance is good when the flying wing is used as a fixed wing; and on the other hand, the structure is compact, and the arrangement of the propellers 5 and the switching of the flight modes of the rotor and the fixed wing are facilitated.
And one pair of the three propellers 5 is symmetrically arranged at the front edge of the wing 1, and the other pair of the three propellers is arranged at the rear edge of the wing 1 and is positioned on the symmetry axis of the wing 1. Three sets of propellers are arranged respectively in wing front and back edge, make unmanned aerial vehicle atress more even, flight at the stage of taking off and landing more stable when as gyroplane flight. In one example, two sets of propellers arranged at the leading edge of the wing are arranged at the spanwise middle position of the wing, and the arrangement mode has low requirement on the rigidity of the structure of the wing 1.
The three tilting mechanisms 7 are respectively used for driving the corresponding propellers 5 to tilt, and can drive the propellers 5 to tilt by more than 90 degrees. In a specific example, the tilting mechanism comprises a controller for monitoring and controlling the tilting angle of the propeller 5. Screw 5 possesses the function of verting through the control of verting mechanism 7 as unmanned aerial vehicle's driving system, provides the lift of vertical direction at unmanned aerial vehicle take-off and land stage, provides the power of horizontal direction at unmanned aerial vehicle normal flight stage. Fig. 1 and 2 show the effect of the propeller in a flipped-up state and a non-flipped-up state, respectively. When the drone is flying in rotor mode during the takeoff and landing phases, the propellers 5 are rotated to a direction where the disk is parallel to the wing, providing lift similar to a helicopter rotor. When the unmanned aerial vehicle flies in a fixed wing mode, the propeller rotates to the direction perpendicular to the propeller disc and the wings, and advancing power is provided.
In the embodiment, a flexible conformal solar cell array 2 is laid on the upper surface of the wing 1, a storage battery 3 is installed inside the unmanned aerial vehicle, and the solar cell array 2 provides electric energy for the storage battery 3; be equipped with the rotatory power motor 6 of drive screw 5 on the unmanned aerial vehicle, power motor 6 is connected with battery 3. Present solar energy unmanned aerial vehicle is mostly fixed wing unmanned aerial vehicle to adopt the take-off and landing mode of level slumping, have higher requirement to runway wind speed wind direction, and can't realize independently hovering and move back specific actions such as flying aloft. This scheme is equipped with solar unmanned aerial vehicle and goes up the rotation rotor that inclines, makes solar unmanned aerial vehicle can switch between stationary vane and rotor. The vertical take-off and landing, hovering, side flying and rear flying of the gyroplane can be realized, and the long-distance long-endurance flying of the fixed-wing aircraft can be realized.
In one embodiment, the tilting mechanism is disposed inside the wing, the tilting mechanism comprising: mount, telescopic machanism and link assembly, mount are fixed on unmanned aerial vehicle, and the root fixed connection of screw is in link assembly, and link assembly is articulated with mount and telescopic machanism's flexible end respectively, and telescopic machanism is used for driving link assembly and rotates to make the screw take place to vert. In this embodiment, the connecting rod assembly is E-shaped, and includes a common connecting portion, a first connecting rod, a second connecting rod, and a third connecting rod; wherein, one side surface of the public connecting part is fixed with the root part of the propeller; the first connecting rod, the second connecting rod and the third connecting rod are arranged in parallel; one end of the first connecting rod and one end of the second connecting rod are respectively connected with two ends of the public connecting part, and the other end of the first connecting rod and the other end of the second connecting rod are respectively hinged with two ends of the top of the fixed frame; one end of the third connecting rod is connected with the middle part of the public connecting part, and the other end of the third connecting rod is hinged with the telescopic end of the telescopic mechanism. The tilting mechanism can also adopt other structural forms as long as the driving propeller can tilt relative to the plane where the wing is located.
In one embodiment, the drone comprises a vertical fin 8, the vertical fin 8 being disposed on an upper surface of a wing tip of the wing 5, and the wing 5 being perpendicular to the vertical fin 8. The vertical fin is used as a vertical stabilizing surface of the unmanned aerial vehicle, the vertical fin adopts a trapezoidal shape, and the pneumatic efficiency is high. In the existing unmanned configuration, there is also a vertical fin, which is generally located on the axis of symmetry of the aircraft, whereas the vertical fin of this embodiment is located slightly above the wing of the outer wing section of the wing, unlike the prior art.
In one embodiment, the unmanned aerial vehicle comprises a landing gear 11, the landing gear 11 is a three-point nose landing gear, two pivot points of the landing gear 11 are arranged on the lower surface of the wing tip of the wing 1 and opposite to the vertical tail 8, and the other pivot point is arranged on the lower surface of the unmanned aerial vehicle and is located on the symmetry axis of the wing 1.
Referring to fig. 1 or 2, in one embodiment the drone comprises a pair of ailerons 9, the pair of ailerons 9 being symmetrically disposed at the trailing edge of the wing 1. The ailerons 9 are respectively arranged on the left and the right to realize the rolling control of the unmanned aerial vehicle.
In one embodiment, the drone comprises a pair of rudders 10, the rudders 10 being provided at the trailing edge of the vertical tail 8. The left and right sides of the rudder 10 are respectively provided with a piece, so that the yaw control of the unmanned aerial vehicle is realized. The ailerons 9 and the rudder 10 are used in combination to effect pitch control of the drone.
In one embodiment, the number of the blades of each propeller 5 is two, and the propellers adopt two-blade propellers, so that the two-blade propellers have higher efficiency when the unmanned aerial vehicle flies in a fixed-wing mode based on the characteristic that the solar unmanned aerial vehicle flies for a long time.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.

Claims (10)

1. The utility model provides a rotor solar energy unmanned aerial vehicle verts, a serial communication port, include:
the wing is of a flying wing structure, and a flexible conformal solar cell array is laid on the upper surface of the wing;
three propellers, wherein one pair of propellers is symmetrically arranged at the front edge of the wing, and the other propeller is arranged at the rear edge of the wing and is positioned on the symmetry axis of the wing;
the three mechanism that verts, every it corresponds with one to vert the mechanism the propeller is connected, it is used for the drive to vert the mechanism the propeller for the plane at wing place verts.
2. The tiltrotor solar drone of claim 1, wherein a battery is mounted inside the drone, the solar array providing electrical power to the battery; and the unmanned aerial vehicle is provided with a power motor for driving the propeller to rotate, and the power motor is connected with the storage battery.
3. The tiltrotor solar unmanned aerial vehicle of claim 1, wherein the tilt mechanism is disposed inside the wing, the tilt mechanism comprising: mount, telescopic machanism and link assembly, the mount is fixed on the unmanned aerial vehicle, the root fixed connection of screw in link assembly, link assembly respectively with the mount reaches telescopic machanism's flexible end is articulated, telescopic machanism is used for the drive link assembly rotates, so that the screw takes place to vert.
4. The tiltrotor solar drone of claim 1, wherein the wing has an aspect ratio greater than 15.
5. The tiltrotor solar drone of claim 1, wherein the drone includes a vertical tail disposed on an upper surface of a wing tip of the wing, and the wing and the vertical tail are mutually perpendicular.
6. The tilt rotor solar drone according to claim 5, wherein the drone includes a landing gear, the landing gear being of the three-point type, two of the fulcrums of the landing gear being arranged on the lower surface of the wing tip of the wing opposite the vertical tail, the other fulcrum being arranged on the lower surface of the drone and lying on the axis of symmetry of the wing.
7. The tiltrotor solar drone of claim 5, wherein the drone includes a pair of ailerons symmetrically disposed at a trailing edge of the wing.
8. The tiltrotor solar drone of claim 5, wherein the drone includes a pair of rudders disposed at a trailing edge of the vertical tail.
9. The tilt-rotor solar drone according to claim 1, wherein the number of blades per propeller is two.
10. The tiltrotor solar drone of claim 1, wherein the tilt mechanism includes a controller for monitoring and controlling the tilt angle of the propeller.
CN202111244275.6A 2021-10-26 2021-10-26 Rotor solar energy unmanned aerial vehicle verts Pending CN113682471A (en)

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CN202111244275.6A CN113682471A (en) 2021-10-26 2021-10-26 Rotor solar energy unmanned aerial vehicle verts

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Application Number Priority Date Filing Date Title
CN202111244275.6A CN113682471A (en) 2021-10-26 2021-10-26 Rotor solar energy unmanned aerial vehicle verts

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115009516A (en) * 2022-05-26 2022-09-06 北京理工大学 Distributed solar tilt rotor unmanned aerial vehicle

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN206634198U (en) * 2017-03-09 2017-11-14 北京天宇新超航空科技有限公司 A kind of inclining rotary mechanism for tiltrotor
CN110104162A (en) * 2019-04-28 2019-08-09 厦门大学 A kind of solar energy flying wing with a variety of landing modes
CN110254720A (en) * 2019-05-31 2019-09-20 中国航天空气动力技术研究院 A kind of Flying-wing's solar energy unmanned plane
CN209553498U (en) * 2019-02-13 2019-10-29 深圳创壹通航科技有限公司 Fixed-wing unmanned plane with VTOL function
CN110579140A (en) * 2019-10-14 2019-12-17 通彩智能科技集团有限公司 Multi-degree-of-freedom automatic adjusting mechanism for missile hanging vehicle
US20200262549A1 (en) * 2017-03-15 2020-08-20 Textron Innovations Inc. Vibration Isolation Systems for Advancing Blade Concept Rotorcraft

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN206634198U (en) * 2017-03-09 2017-11-14 北京天宇新超航空科技有限公司 A kind of inclining rotary mechanism for tiltrotor
US20200262549A1 (en) * 2017-03-15 2020-08-20 Textron Innovations Inc. Vibration Isolation Systems for Advancing Blade Concept Rotorcraft
CN209553498U (en) * 2019-02-13 2019-10-29 深圳创壹通航科技有限公司 Fixed-wing unmanned plane with VTOL function
CN110104162A (en) * 2019-04-28 2019-08-09 厦门大学 A kind of solar energy flying wing with a variety of landing modes
CN110254720A (en) * 2019-05-31 2019-09-20 中国航天空气动力技术研究院 A kind of Flying-wing's solar energy unmanned plane
CN110579140A (en) * 2019-10-14 2019-12-17 通彩智能科技集团有限公司 Multi-degree-of-freedom automatic adjusting mechanism for missile hanging vehicle

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115009516A (en) * 2022-05-26 2022-09-06 北京理工大学 Distributed solar tilt rotor unmanned aerial vehicle

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Application publication date: 20211123