CN110683030B - An unmanned aerial vehicle capable of vertical take-off and landing - Google Patents
An unmanned aerial vehicle capable of vertical take-off and landing Download PDFInfo
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- CN110683030B CN110683030B CN201911024319.7A CN201911024319A CN110683030B CN 110683030 B CN110683030 B CN 110683030B CN 201911024319 A CN201911024319 A CN 201911024319A CN 110683030 B CN110683030 B CN 110683030B
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- fuselage
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- vertical tail
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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
- B64C27/22—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
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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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
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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
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
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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
- B64D27/40—Arrangements for mounting power plants in aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention belongs to the aircraft design technology, and particularly relates to an unmanned aircraft capable of taking off and landing vertically. In order to get rid of the constraint of the rotor craft mode, the invention combines various flight characteristics of a rotor and a fixed wing aircraft, and the proposed vertical take-off and landing unmanned aerial vehicle comprises a fuselage, wings, a duck wing, a vertical tail, an electric engine and a fuel engine, wherein the fuselage comprises a left fuselage and a right fuselage which are connected at the front end through the duck wing, at the rear end through an inner wing, at the outer end, the fuel engine comprising the rotor is arranged at the rear end, the vertical tail is arranged at the upper side and the lower side of the rear end, the electric engine comprising the rotor is arranged at the tip of the vertical tail, the rear edge of the wing is provided with a flap and an aileron, and the rear edge of the vertical tail is provided with a rudder. The cost is greatly reduced, a larger load space is provided, and the task requirement of large load transportation of the aircraft can be met. The oil consumption is lower, and the wind resistance is effectively improved when the oil is vertical.
Description
Technical Field
The invention belongs to the aircraft design technology, and particularly relates to an unmanned aircraft capable of taking off and landing vertically.
Background
The conventional rotor craft has low flying speed and short range, has limited carrying capacity, improves the flying speed, increases the flying range, increases the load transportation capacity, and is always a popular field for rotor craft research. Compared with other rotor craft, the tailstock type vertical take-off and landing aircraft has the advantages of symmetrical aerodynamic characteristics, good maneuverability, compact structure, high hovering performance and the like, and is more suitable for occasions with larger take-off and landing site limit and strong hovering performance and maneuverability requirements. The method has the advantages of large application space and good application prospect, can play a remarkable role in various military tasks such as reconnaissance, early warning, attack and unconventional combat conditions, plays an irreplaceable important role in the future military field, is a main participant in the future war, and can play a unique role in related important civil fields such as electric power line inspection, dam detection, traffic accident investigation and the like.
Disclosure of Invention
The invention aims to solve the technical problems of providing a tailstock type high-efficiency aircraft capable of taking off and landing vertically, which gets rid of the constraint of a rotor aircraft mode, integrates various flight characteristics of a rotor and a fixed-wing aircraft, has various flight control instructions and various key flight task modes, and can realize the task of completing a large load of a vertical take-off and landing unmanned aerial vehicle.
The technical scheme is that the aircraft comprises a fuselage, wings, duckwings, a vertical tail, an electric engine and a fuel engine, wherein the fuselage comprises a left fuselage and a right fuselage, the left fuselage and the right fuselage are connected at the front end through the duckwings, the rear end is connected through the inner side wings, the outer end is provided with the wings, the fuel engine comprising a rotor wing is arranged at the rear end, the vertical tail is arranged at the upper side and the lower side of the rear end, the electric engine comprising the rotor wing is arranged at the tip of the vertical tail, the rear edge of the wing is provided with a flap and an aileron, and the rear edge of the vertical tail is provided with a rudder.
Furthermore, the fuselage and the wing adopt a wing body fusion design, and are symmetrical by the longitudinal symmetry plane of the airplane.
Furthermore, the heads of the left machine body and the right machine body are respectively in semitransparent design, namely an infrared photoelectric camera cabin and a visible photoelectric camera cabin.
Further, the wing is a middle single trapezoid wing, a wing tip is provided with a wing tip winglet, a supporting rod for assisting in vertical lifting is arranged below the wing tip winglet, the wing is smooth and excessive to the wing surface, and the bottom end of the electric engine is provided with a supporting rod for vertical lifting.
Furthermore, the duck wings are flat wings, the two sides of the duck wings and the machine body are designed in a smooth transition mode, and the trailing edge of the duck wings is provided with an elevator.
Further, the tail is swept at a angle of 40 degrees after 1/4 chord line.
Further, the fuselage interior also includes a flight control system, a power supply system, and an emergency recovery device.
Further, during the vertical take-off and landing stage, the electric engine and the fuel engine provide aircraft lift, the horizontal attitude is controlled by asymmetric thrust provided by the engines, and the transverse heading attitude control of the aircraft is controlled by rudders and asymmetric thrust at the trailing edge of the vertical tail.
Further, during the transition stage, the attitude of the aircraft is adjusted through the asymmetric thrust provided by the electric engine and the rudder at the trailing edge of the vertical tail, and when the engine body reaches a certain speed to generate effective aerodynamic force, the system stability is jointly maintained by combining each control surface with six rotors.
Further, in the forward flight stage, the heading is controlled through a rudder, the rolling gesture is controlled through an aileron, the body gesture is regulated through a self-balancing system, the lifting motion is controlled through an elevator, and the electric engine stops working.
The vertical take-off and landing aircraft has the beneficial effects that the thrust direction of the aircraft is always consistent with the movement direction of the aircraft body, so that the thrust of the engine is in the vertical direction in the take-off and landing stage, the thrust of the engine is in the front flight direction in the cruising stage, a thrust conversion structure is not needed, the change of the flight attitude is carried out only by virtue of the flight control system, the purpose of entering a flat flight cruising mode from the vertical take-off and landing mode is achieved, the vertical take-off and landing unmanned aircraft with the structure being simpler than a tilting force is achieved, and the safety and the reliability are higher.
The double-fuselage allows the nacelle shape-preserving outer cover to be designed by adopting two different light-transmitting materials, namely visible light and infrared light, so that compared with the shape-preserving materials used by the independent nacelle design required by the same performance, the cost is greatly reduced, and meanwhile, the design of the double-fuselage provides a larger load space for the aircraft, so that the task requirement of large load transportation of the aircraft can be realized.
The double-oil-driven engine increases the control allowance of the transverse direction of the vertical take-off and landing unmanned aerial vehicle during take-off, improves the wind resistance, has lower oil consumption, smaller engine size and relatively smaller resistance of a machine body design compared with a single-engine design for providing the same thrust, and effectively improves the wind resistance when the design of the duck wings is vertical.
Drawings
FIG. 1 is a schematic view of the structure of a vertically-taking-off and landing unmanned aerial vehicle of the present invention;
FIG. 2 is a schematic illustration of a vertical takeoff and landing phase of a vertically-landing unmanned aerial vehicle of the present invention;
Fig. 3 is a schematic top view of the forward flight phase of the vertically-taking-off and landing unmanned aerial vehicle of the present invention.
Wherein, 1-fuselage, 2-wing, 3-duck wing, 4-vertical tail, 5-motor engine and 6-fuel engine
Detailed Description
Referring to fig. 1, the vertical take-off and landing unmanned aerial vehicle of the present invention includes a fuselage 1, wings 2, a duck wing 3, a vertical tail 4, an electric motor 5 and a fuel engine 6. The unmanned aerial vehicle capable of taking off and landing vertically adopts a duck-shaped layout and a pneumatic layout of single wings in a double-fuselage, and the fuselage, the wings 2 and the fuselage and the duck wings 3 all adopt a wing body fusion design.
The machine body 1 is of a double-machine body design and comprises a left machine body and a right machine body which are symmetrical relative to the longitudinal symmetry plane of the airplane, vertical tails 4 are respectively arranged at the upper side and the lower side of the tail parts of the left machine body and the right machine body, wing body fusion design is adopted at the joint part, two head parts of the left machine body and the right machine body are photoelectric camera cabins, semitransparent design is adopted, infrared light and visible light different light-transmitting materials are respectively adopted for aiming and transmitting or investigation, a fuel engine 6 is arranged at the tail parts of the left machine body and the right machine body and provided with a rotor wing, and the middle parts of the left machine body and the right machine body are used for arranging batteries, oil tanks, flight control systems, power supplies, electric systems and the like.
The wing 2 is a middle single trapezoid wing, a low-speed high-lift wing section Naca Ls-0417mod is adopted as a wing root, benedek 8405A is adopted as a wing tip wing section, the installation angle is 3 degrees, the dihedral angle is 0 degree, the torsion angle is 3 degrees, the tip root ratio is 0.32, the lift aileron is arranged at the rear edge, and a design support rod at the wing tip is smooth and excessive with the wing surface. Benedek10355B wing profiles are adopted between the left body and the right body. The wing part structure is designed by adopting a double beam, the reinforcing ribs are designed on the wing root and the wing tip, the rib plates are uniformly distributed on the rest parts, and the skin is made of carbon fiber glass fiber reinforced plastic material and is integrally formed.
The duck wing 3 is arranged at the front ends of the middle parts of the left machine body and the right machine body, adopts straight wings, middle single wings, the installation angle is 2 degrees, the length is slightly longer than 1, the length is extended by 850cm, and the trailing edge is provided with an elevator.
The vertical tails 4 are symmetrically arranged on the upper side and the lower side of the left fuselage and the right fuselage, the sweepback angle of 1/4 chord line is 40 degrees, the aspect ratio is 11, the tip-root ratio is 0.55, electric engines 5 with rotor wings are arranged at the wing tips of the vertical tail wings on the upper side and the lower side, and the rear edges of the vertical tail wings on the two sides are provided with rudders.
The electric engine 5 is divided into two parts, wherein the upper section of the electric engine is parabolic and wraps a paddle inserting disc, the lower section of the electric engine is parabolic and wraps an internal motor to form an electric engine cabin, the tail section of the electric engine is provided with a supporting rod, and four groups of rotary wings are equidistant and symmetrical with each other about the central axis of the unmanned aerial vehicle. The optimal scheme is that four groups of rotary wings are distributed in a square shape.
Table 1 is the main performance index of the vertical takeoff and landing unmanned aerial vehicle.
TABLE 1
In the vertical take-off and landing stage, as shown in fig. 2, four electric engines 5 and a fuel engine 6 at the tail part of the airplane body provide airplane lift force, the horizontal attitude is controlled by the asymmetry of engine thrust, and the transverse heading attitude control of the airplane is controlled by the rudder at the trailing edge of the vertical tail and the power asymmetry of the airplane bodies at two sides.
And in the transition stage, the asymmetric thrust provided by the electric engine 5 and the rotation of the vertical tail trailing edge rudder realize the horizontal and height direction movement, the body is stable in posture through a self-balancing system, and when the body reaches a certain speed and generates effective aerodynamic force, the rudder, the elevator and the aileron at the trailing edge of the outer wing are connected, so that the stability of the system is maintained together with the four rotors.
In the forward flight stage, the heading is controlled by a rudder, the rolling gesture is controlled by an aileron, the body gesture is regulated by a self-balancing system, and the lifting motion is controlled by an elevator.
Claims (7)
1. The unmanned aerial vehicle capable of taking off and landing vertically is characterized by comprising a body (1), wings (2), a duck wing (3), a vertical tail (4), an electric engine (5) and a fuel engine (6), wherein the body comprises a left body and a right body which are connected at the front end through the duck wing (3), are connected at the rear end through an inner wing, are provided with the wings (2) at the outer end, are provided with the fuel engine (6) comprising the rotors at the rear end, are provided with the vertical tail (4) at the upper side and the lower side of the rear end, are provided with the electric engine (5) comprising the rotors at the tip of the vertical tail (4), are provided with support rods for taking off and landing vertically, the rear edge of the wings (2) is provided with flaps and ailerons, and the rear edge of the vertical tail (4) is provided with rudders;
In the vertical take-off and landing stage, the electric engine (5) and the fuel engine (6) provide aircraft lift force, the horizontal attitude is controlled by asymmetric thrust provided by the engines, and the horizontal attitude control of the aircraft is controlled by a rudder at the trailing edge of the vertical tail and the asymmetric thrust;
in the transition stage, the attitude of the aircraft is adjusted through the asymmetric thrust provided by the motor engine (5) and the rudder at the trailing edge of the vertical tail, and when the engine body reaches a certain speed to generate effective aerodynamic force, the system stability is jointly maintained by combining each control surface with six rotors;
In the forward flight stage, the heading is controlled by a rudder, the rolling gesture is controlled by an aileron, the body gesture is regulated by a self-balancing system, the lifting motion is controlled by an elevator, and the electric engine (5) stops working.
2. The unmanned aerial vehicle capable of taking off and landing vertically according to claim 1, wherein the fuselage (1) and the wing are designed in a wing-body fusion manner and are symmetrical with respect to the longitudinal symmetry plane of the aircraft.
3. The unmanned aerial vehicle capable of taking off and landing vertically according to claim 1, wherein the heads of the left fuselage and the right fuselage are respectively of semitransparent design, namely an infrared photoelectric camera cabin and a visible photoelectric camera cabin.
4. The unmanned aerial vehicle capable of taking off and landing vertically according to claim 1, wherein the wing (2) is a middle single trapezoid wing, the wing tip is designed with a wingtip winglet, and a supporting rod for assisting in taking off and landing vertically is arranged below the wingtip winglet and is in smooth transition with the wing surface.
5. The unmanned aerial vehicle capable of taking off and landing vertically according to claim 1, wherein the duck wings (3) are straight wings, two sides and the fuselage are designed in a smooth transition manner, and the trailing edge is provided with an elevator.
6. The unmanned aerial vehicle of claim 1, wherein the vertical tail (4) is swept at a line sweep angle of 1/4 of 40 degrees.
7. The unmanned aerial vehicle capable of taking off and landing vertically according to claim 1, wherein the fuselage (1) further comprises a flight control system, a power supply system and an emergency recovery device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911024319.7A CN110683030B (en) | 2019-10-25 | 2019-10-25 | An unmanned aerial vehicle capable of vertical take-off and landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911024319.7A CN110683030B (en) | 2019-10-25 | 2019-10-25 | An unmanned aerial vehicle capable of vertical take-off and landing |
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| Publication Number | Publication Date |
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| CN110683030A CN110683030A (en) | 2020-01-14 |
| CN110683030B true CN110683030B (en) | 2024-12-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911024319.7A Active CN110683030B (en) | 2019-10-25 | 2019-10-25 | An unmanned aerial vehicle capable of vertical take-off and landing |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112607012A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Vertical take-off and landing fixed wing unmanned aerial vehicle and take-off and landing method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205440869U (en) * | 2016-03-31 | 2016-08-10 | 西安东锐航空科技有限公司 | Fixed chord flight time aircraft of canard configuration of VTOL |
| CN206511122U (en) * | 2017-02-13 | 2017-09-22 | 深圳市龙云创新航空科技有限公司 | A kind of VTOL Fixed Wing AirVehicle |
| CN211223827U (en) * | 2019-10-25 | 2020-08-11 | 中国航空工业集团公司西安飞行自动控制研究所 | A vertical take-off and landing unmanned aerial vehicle |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| CN102897319A (en) * | 2012-08-10 | 2013-01-30 | 江闻杰 | Fuselage variant type vertical take off and landing aircraft |
| CN104290906B (en) * | 2014-11-04 | 2016-05-25 | 中国人民解放军国防科学技术大学 | A kind of vertically taking off and landing flyer |
| US10301016B1 (en) * | 2016-08-09 | 2019-05-28 | Vimana, Inc. | Stabilized VTOL flying apparatus and aircraft |
| CN106927040A (en) * | 2017-02-21 | 2017-07-07 | 西安爱生技术集团公司 | It is a kind of can VTOL the rotor tailless configuration aircraft of tailstock formula four |
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2019
- 2019-10-25 CN CN201911024319.7A patent/CN110683030B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205440869U (en) * | 2016-03-31 | 2016-08-10 | 西安东锐航空科技有限公司 | Fixed chord flight time aircraft of canard configuration of VTOL |
| CN206511122U (en) * | 2017-02-13 | 2017-09-22 | 深圳市龙云创新航空科技有限公司 | A kind of VTOL Fixed Wing AirVehicle |
| CN211223827U (en) * | 2019-10-25 | 2020-08-11 | 中国航空工业集团公司西安飞行自动控制研究所 | A vertical take-off and landing unmanned aerial vehicle |
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| CN110683030A (en) | 2020-01-14 |
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