CN112810812A - Combined type VTOL long-endurance electric unmanned aerial vehicle - Google Patents
Combined type VTOL long-endurance electric unmanned aerial vehicle Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention discloses a combined type vertical take-off and landing long-endurance electric unmanned aerial vehicle, and belongs to the field of unmanned aerial vehicles. According to the combined type vertical take-off and landing long-endurance electric unmanned aerial vehicle, the body adopts the wing body fusion body, unnecessary exposed parts of the body are removed, the wetted area of the aircraft can be reduced, and therefore the friction resistance is reduced, and the lift-drag ratio of the unmanned aerial vehicle is improved by reducing parts irrelevant to the lift force through the wing body fusion layout; the invention adopts the wingtip winglet and utilizes the end plate effect of the wingtip winglet to increase the equivalent aspect ratio of the airplane under the condition of small increase of the wingspan. The invention adopts the layout of the double tail support empennages, can improve the lateral stability of the unmanned aerial vehicle and has better structural support. According to the invention, the lift-drag ratio pneumatic layout is improved through the structural design of the unmanned aerial vehicle, so that the endurance performance of the airplane is improved.
Description
Technical Field
The invention belongs to the field of unmanned aerial vehicles, and particularly relates to a combined type vertical take-off and landing long-endurance electric unmanned aerial vehicle.
Background
In recent ten years, the related technology of the unmanned aerial vehicle is rapidly developed, and the unmanned aerial vehicle gradually enters the public visual field from the original military field and is colorful in the civil field. Along with a large amount of researcher's joining, unmanned aerial vehicle configuration is more and more, fixed wing unmanned aerial vehicle, rotor unmanned aerial vehicle, combined type unmanned aerial vehicle and so on, and the usage is also more and more extensive, extensively is used for agriculture and forestry plant protection, electric power inspection, meteorological observation, city environmental monitoring, express delivery freight transportation, taking photo by plane and so on. For the unmanned aerial vehicle inspection industry, the fixed-wing unmanned aerial vehicle has the advantages of high flying speed, large cruising area, load carrying capacity of tasks and the like, but the fixed-wing unmanned aerial vehicle needs runway running for taking off and landing, has certain requirements on the field, cannot hover to acquire images of a certain continuous position, and is high in operation difficulty. Many rotor unmanned aerial vehicle has small, and light in weight can not need the place to carry out VTOL, easily the operation of going up to the hand, but its flying speed is little, and flying distance is short for aerial survey efficiency is very low. And combined type unmanned aerial vehicle, the advantage that has possessed stationary vane and rotor unmanned aerial vehicle simultaneously, not only can realize VTOL function, need not the place requirement, can also realize that the fixed point hovers and obtain the continuous image in certain department, can also carry on load and flying speed is fast, cruising distance is far away, it is efficient to patrol and examine, nevertheless because the restriction of aircraft battery, common combined type VTOL unmanned aerial vehicle duration is probably about 60 to 100 minutes on the existing market, this just makes to long distance, when patrolling and examining the task by a large scale, have to use many times of flights to accomplish the task, so how to improve unmanned aerial vehicle's duration and have very important meaning.
Disclosure of Invention
The invention aims to overcome the defect that the endurance time of an unmanned aerial vehicle is limited, and provides a combined type vertical take-off and landing long-endurance electric unmanned aerial vehicle.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
a combined type vertical take-off and landing long-endurance electric unmanned aerial vehicle comprises a body, an airspeed head and a thrust propeller;
the fuselage adopts a wing body fusion body, wings are arranged on two sides of the fuselage, and wingtips winglets are arranged at the tail ends of the wings;
a rotor arm is arranged below each wing, and each rotor arm is of a box-type structure;
the tail part of the machine body is provided with a thrust propeller;
an empennage is arranged between the two rotor arms and adopts double tail supports;
the unmanned aerial vehicle is characterized in that a four-axis rotor system is arranged on the body and used for realizing vertical take-off, landing and hovering of the unmanned aerial vehicle; a main propeller power system is loaded at the tail of the aircraft body, and a fixed wing flat flight mode is carried out through the power system; fuselage internally loaded has unmanned aerial vehicle's flight control system.
Further, the wings are trapezoidal straight wings;
the wing has an installation angle of 2-3 degrees and a sweep angle of 10 degrees.
Further, the wing comprises a left wing and a right wing, the left wing and the right wing are respectively connected with the fuselage through a wing girder, and the wing girder is located at the 1/4 chord length position of the wing.
Furthermore, the wingtip winglet comprises a left wingtip winglet and a right wingtip winglet which are respectively connected with the wing through the wing main girder.
Further, the rotor arms are located at an extended position 16% of the span of the wing from the root.
Furthermore, the inside power supply spare that is used for depositing four-axis rotor system of box body of rotor horn.
Furthermore, the flight control system is located at the center of gravity of the airplane body.
Furthermore, the nose of the airplane body is provided with an airspeed head for measuring the flying speed of the airplane.
Compared with the prior art, the invention has the following beneficial effects:
according to the combined type vertical take-off and landing long-endurance electric unmanned aerial vehicle, the body adopts the wing body fusion body, the friction resistance of the unmanned aerial vehicle is in a linear relation with the whole-aircraft wetted area, unnecessary exposed parts of the body are removed, the wetted area of the aircraft can be reduced, and therefore the friction resistance is reduced, and the lift-drag ratio of the unmanned aerial vehicle is improved by reducing parts irrelevant to the lift force through the wing body fusion layout; the increase of the wingspan of the airplane is limited by factors such as wing strength, rigidity, flying speed and the like, and the length of the wingspan cannot be increased infinitely. The rotor wing horn is designed into a box structure, a power source part of a four-axis rotor wing system can be placed in the box body, because the lift force generated by the wing can generate bending moment at the root of the wing, the longer the wing span is, the larger the bending moment is, a heavy object can be placed in the box body of the rotor wing horn to provide gravity opposite to the direction of the lift force, and the downward bending moment generated at the root of the wing can offset part of the bending moment generated by the lift force, so that the length of the wing span can be longer under the same strength and rigidity; the larger the aspect ratio of the airplane is, the smaller the induced resistance generated by the wings is, and the high-aspect ratio wings are adopted to reduce the induced resistance so as to improve the endurance performance; according to the invention, the thrust propeller is designed behind the fuselage, so that the reduction of the lift-drag characteristic of the wing caused by the slipstream of the propeller can be avoided, and the lift-drag characteristic of the unmanned aerial vehicle is greatly improved; the invention adopts the layout of the double tail support empennage, can improve the lateral stability of the unmanned aerial vehicle, has better structural support, can realize larger wingspan design, is very suitable for the unmanned aerial vehicle in long endurance, and simultaneously, the airflow generated by the thrust propeller at the tail part of the body can not influence the empennage. According to the invention, the lift-drag ratio pneumatic layout is improved through the structural design of the unmanned aerial vehicle, so that the endurance performance of the airplane is improved.
Further, the thrust screw is established at the fuselage back, and the airspeed head is installed in aircraft nose dead ahead to avoid the influence of screw slipstream to airspeed sensor, make airspeed measurement result precision higher. In addition, equipment such as a flight controller or a camera and the like needs to be installed in front of the machine head, the equipment is sensitive to vibration, and the influence of motor vibration on the equipment can be effectively reduced by adopting a propeller rear propulsion layout.
Drawings
FIG. 1 is an overall view of the present invention;
FIG. 2 is a front view of the present invention;
FIG. 3 is a top view of the present invention;
fig. 4 is a right side view of the present invention.
Wherein: 1-wingtip winglet, 2-wing, 3-fuselage, 4-airspeed tube, 5-thrust propeller, 6-empennage, 7-rotor wing arm, and 8-four-axis rotor wing system.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
Patrol and examine unmanned aerial vehicle and require to have long enough time of cruising so that can accomplish more shooting tasks in less overhead flight, save time cost, so carry out the analysis to VTOL unmanned aerial vehicle cruise stage:
as shown in fig. five, unmanned aerial vehicle patrols and navigates the level flight in-process, then has according to the balanced principle of power then, and lift equals gravity, and thrust is to the resistance:
L＝G
T＝D
assuming that the total available thrust energy of the aircraft is Q, the total power used by the aircraft in flight is P _ all, and P _ v is the power used to overcome the drag, the following efficiencies can be obtained:
the duration of the flight is
The lift is expressed by utilizing the air density, the speed, the wing area and the lift coefficient, and the speed item is converted into the lift coefficient:
the resistance D can also be expressed as:
the endurance time t can be expressed as:
after simplification, the following steps are carried out:
wherein the content of the first and second substances,
called power factor, the longer the power factor reaches the maximum value; measures are therefore taken against the increase in lift and the reduction in drag of the VTOL drone.
The invention is described in further detail below with reference to the accompanying drawings:
the combined type vertical take-off and landing long-endurance electric unmanned aerial vehicle adopts a combined type propulsion system, has two flight modes of vertical take-off and landing and endurance flat flight, has the vertical take-off and landing and hovering operation capabilities similar to a helicopter, has the advantages of high flying speed and large load capacity of a fixed wing aircraft, and can realize long-endurance flight.
Referring to fig. 1-4, fig. 1-4 are an overall view, a front view, a top view and a right view of the hybrid vertical take-off and landing electric unmanned aerial vehicle of the present invention, respectively, and the hybrid vertical take-off and landing electric unmanned aerial vehicle of the present invention comprises a winglet 1, a wing 2, a fuselage 3, an airspeed head 4, a thrust propeller 5, a tail wing 6, a rotor arm 7 and a four-axis rotor system 8;
the fuselage 3 adopts a wing body fusion body, the wings 2 are arranged on two sides of the fuselage 3, and wingtips winglets 1 are arranged at the tail ends of the wings 2; a rotor arm 7 is respectively arranged below the wings 2, and the rotor arms 7 are box-shaped structures and used for placing power source components such as batteries and the like; the left rotary wing arm is positioned below the left wing, and the right rotary wing arm is positioned below the right wing; the airspeed head 4 is positioned at the head of the fuselage 3 and is used for measuring the flying speed of the airplane; the thrust propeller 5 is positioned at the tail part of the machine body 3, and the tail wing 6 is arranged between two rotor wing arms 7 and adopts a double tail boom layout; the four-axis rotor system 8 is arranged on the machine body 3, so that functions of vertical take-off and landing, hovering and the like of the unmanned aerial vehicle are realized; the tail part of the machine body 3 is provided with a main propeller power system, and a fixed wing horizontal flight mode is carried out through an electric power system; fuselage 3 internal loading has unmanned aerial vehicle navigation control equipment.
The wing 2 is a trapezoidal straight wing with a large aspect ratio; the wing 2 comprises a left wing and a right wing, the left wing and the right wing are respectively connected with the fuselage 3 through a main beam of the wing 2, the main beam of the wing 2 is positioned at the 1/4 chord length position of the wing, the wing 2 has an installation angle, the installation angle is 2-3 degrees, the wing 2 has a small sweep angle, and the sweep angle is 10 degrees. And the trailing edges of the left wing and the right wing are respectively provided with an aileron. Besides frictional resistance, another resistance source of the cruising flight of the airplane is induced resistance generated by wings and other components when generating lift force, the reduction of the induced resistance of the wings of the unmanned aerial vehicle has great influence on the improvement of the cruising performance of the airplane, and under the condition that other wing design parameters are the same, the larger the aspect ratio of the airplane is, the smaller the induced resistance generated by the wings is.
The wingtip winglet 1 comprises a left wingtip winglet and a right wingtip winglet which are respectively connected with the wings 2 through the main beams of the wings 2, and the equivalent aspect ratio of the airplane is increased under the condition that the wingspan increase is small by utilizing the end plate effect of the wingtip winglet, so that the lift-drag ratio of the whole airplane body is improved, and the cruising performance of the airplane is improved.
Thrust screw 5 is located 3 afterbody of fuselage, establishes thrust screw 3 and can install airspeed tube 4 in the aircraft nose dead ahead behind fuselage 3 to avoid the influence of screw slipstream to airspeed sensor, make airspeed measurement result precision higher. In addition, equipment such as a flight controller or a camera and the like needs to be installed in front of the machine head, the equipment is sensitive to vibration, and the influence of motor vibration on the equipment can be effectively reduced by adopting a propeller rear propulsion layout.
The empennage 6 is connected with the box-type rotor wing horn 7, so that the maneuverability and the stability of the airplane can be improved, the horizontal empennage controls the lifting of the unmanned aerial vehicle, and the vertical direction controls the yawing of the unmanned aerial vehicle.
The rotor wing horn 7 is located 2 spanwise distances 16% span length of wing root of wing to pass through bolted connection with 2 lower surfaces of wing, the inside power source spare that is used for depositing four-axis rotor system 8 of box body of rotor wing horn 7, the moment of flexure that the downward gravity of rotor wing horn 7 arouses at the wing root offsets with the moment of flexure that 2 surface lift of wing produced at the wing root, thereby the aspect ratio of increase aircraft that can be as big as possible.
Four-axis rotor system 8 is located rotor horn 7 both ends, and the motor rotates the drive screw and produces lift, control unmanned aerial vehicle's the motion of vertical direction.
Unmanned aerial vehicle's flight control system places in fuselage 3 inside, is located the focus position of fuselage 3.
The composite vertical take-off and landing long-endurance electric unmanned aerial vehicle has two modes of vertical take-off and landing and cruising flight. Under the VTOL state, the propeller that is located the brushless DC motor drive four-axis rotor system 8 on rotor horn 7 rotates, and four-axis rotor system 8 produces lift and carries out the flight control, and thrust propeller 5 is out of work. Under the state of cruising, unmanned aerial vehicle flies with cruising speed level, and four-axis rotor system 8 stop work, relies on wing 2 to produce lift this moment, and motor drive thrust screw 8 in the fuselage 3 produces thrust, overcomes flight resistance. When unmanned aerial vehicle is in the state of cruising, the lift-drag ratio of whole machine is higher, and thrust motor power consumption is lower, multiplicable cruise time, improvement when navigating. The invention has the vertical take-off and landing and hovering operation capability and can realize long-endurance flight in a cruise flight state.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (8)
1. A combined type vertical take-off and landing long-endurance electric unmanned aerial vehicle is characterized by comprising a vehicle body (3), an airspeed head (4) and a thrust propeller (5);
the fuselage (3) adopts a wing body fusion body, wings (2) are arranged on two sides of the fuselage (3), and wingtips winglets (1) are arranged at the tail ends of the wings (2);
a rotor arm (7) is respectively arranged below the wings (2), and the rotor arms (7) are of box-type structures;
the tail part of the machine body (3) is provided with a thrust propeller (5);
an empennage (6) is arranged between the two rotor arms (7), and the empennage (6) adopts a double tail boom layout;
a four-axis rotor system (8) is arranged on the fuselage (3) and is used for realizing vertical take-off, landing and hovering of the unmanned aerial vehicle; the tail part of the aircraft body (3) is provided with a main propeller power system, and a fixed wing level flight mode is carried out through the power system; fuselage (3) inside loading has unmanned aerial vehicle's flight control system.
2. The hybrid VTOL Long endurance electric UAV according to claim 1, wherein the wings (2) are trapezoidal straight wings;
the wing (2) has an installation angle of 2-3 degrees and a sweep angle of 10 degrees.
3. The hybrid VTOL long endurance electric UAV of claim 2, wherein the wing (2) comprises a left wing and a right wing, the left wing and the right wing are connected to the fuselage (3) through a wing (2) girder, respectively, and the wing (2) girder is located at 1/4 chord length of the wing.
4. The hybrid vertical take-off and landing long-endurance electric unmanned aerial vehicle according to claim 2, wherein the winglet (1) comprises a left winglet and a right winglet, each connected to a wing (2) by a wing (2) main beam.
5. The hybrid VTOL LONG-AEROV according to claim 2, characterized in that the rotorcraft arms (7) are located at an extension of the wings (2) with a distance of 16% from the wing root.
6. The hybrid VTOL Long endurance electric UAV according to claim 5, wherein the rotor arms (7) have a box inside which the power source of the four-axis rotor system (8) is stored.
7. The hybrid VTOL long endurance electric UAV according to claim 1, wherein the flight control system is located at the center of gravity of the fuselage (3).
8. The hybrid vertical take-off and landing long endurance electric unmanned aerial vehicle according to claim 1, wherein the nose of the fuselage (3) is provided with an airspeed head (4) for measuring the flight speed of the aircraft.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110099826.8A CN112810812A (en) | 2021-01-25 | 2021-01-25 | Combined type VTOL long-endurance electric unmanned aerial vehicle |
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| CN202110099826.8A CN112810812A (en) | 2021-01-25 | 2021-01-25 | Combined type VTOL long-endurance electric unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815841A (en) * | 2021-10-21 | 2021-12-21 | 北京航空航天大学 | Long-endurance airplane |
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| CN109131865A (en) * | 2017-06-19 | 2019-01-04 | 贝尔直升机德事隆公司 | Recoverable and extensible flying rotor system |
| CN109319110A (en) * | 2018-10-26 | 2019-02-12 | 安徽云翼航空技术有限公司 | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure |
| CN209225395U (en) * | 2018-10-26 | 2019-08-09 | 安徽云翼航空技术有限公司 | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure |
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2021
- 2021-01-25 CN CN202110099826.8A patent/CN112810812A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105173073A (en) * | 2015-10-08 | 2015-12-23 | 西北工业大学深圳研究院 | Composite lift force type unmanned aerial vehicle realizing vertical take-off and landing |
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| CN106741919A (en) * | 2016-12-21 | 2017-05-31 | 顺丰科技有限公司 | A kind of fixed-wing unmanned plane of VTOL |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815841A (en) * | 2021-10-21 | 2021-12-21 | 北京航空航天大学 | Long-endurance airplane |
| CN113815841B (en) * | 2021-10-21 | 2023-05-26 | 北京航空航天大学 | Long-endurance airplane |
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