CN113788143A - Tail sitting type vertical take-off and landing solar unmanned aerial vehicle - Google Patents
Tail sitting type vertical take-off and landing solar unmanned aerial vehicle Download PDFInfo
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- CN113788143A CN113788143A CN202111344745.6A CN202111344745A CN113788143A CN 113788143 A CN113788143 A CN 113788143A CN 202111344745 A CN202111344745 A CN 202111344745A CN 113788143 A CN113788143 A CN 113788143A
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- unmanned aerial
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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
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a tail-sitting type vertical take-off and landing solar unmanned aerial vehicle, which comprises: a body; the wing is connected with the fuselage, and the wing tip of the wing inclines towards the upper part of the fuselage; the solar cell panel is arranged on the upper surface of the wing; the power structure is arranged on the wingtip of the wing; the undercarriage is arranged at the tail part of the power structure and the tail part of the airframe; the device can not only vertically take off and land without depending on the design of an airport runway through a power structure, but also hover at a fixed point above a target and fly for a long distance.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a tail-sitting type vertical take-off and landing solar unmanned aerial vehicle.
Background
The solar unmanned aerial vehicle is an electric aircraft taking solar radiation as energy, has high flying height, long flying time and long flying distance, but has low wing load, low flying speed and weak wind resistance, and has larger safety risk in the taking-off and landing stages. The existing solar unmanned aerial vehicle at home and abroad mostly adopts a horizontal sliding take-off and landing mode, and the solar unmanned aerial vehicle has the following defects: (1) the use is limited depending on the taking off and landing of the airport runway; (2) the large crosswind can not exist in the taking-off and landing stage, otherwise, the wind easily rushes out of the runway; (3) specific actions such as autonomous hovering, retreating and side flying cannot be realized in the air.
Disclosure of Invention
The invention aims to provide a tail-sitting type vertical take-off and landing solar unmanned aerial vehicle, aiming at the defects in the prior art, which can not only vertically take-off and landing without depending on the design of an airport runway through a power structure, but also hover at a fixed point above a target and fly for a long distance.
In order to achieve the above object, the present invention provides a tail-seated vertical take-off and landing solar unmanned aerial vehicle, comprising:
a body;
the wing is connected with the fuselage, and the wing tip end of the wing inclines towards the upper part of the fuselage;
the solar cell panel is arranged on the upper surface of the wing;
the power structure is arranged on the wingtip of the wing;
and the undercarriage is arranged at the tail part of the power structure and the tail part of the airframe.
Optionally, the fuselage is a short-cabin fuselage, the wings include a left wing and a right wing that are symmetrical to each other, and the fuselage is disposed right below a symmetrical plane of the left wing and the right wing.
Optionally, the wing is in a high aspect ratio all-wing configuration, and the wing is a rectangular wing with upper and lower equal chord lengths.
Optionally, two ailerons are symmetrically arranged on the trailing edge of the wing.
Optionally, a flexible thin film solar cell panel is arranged on the upper surface of the wing.
Optionally, a storage battery is arranged in the wing, and the storage battery is connected with the solar cell panel and the power structure.
Optionally, the landing gear is a retractable landing gear.
Optionally, the power structure comprises:
the power cabin is arranged on the wingtips of the wings;
the propeller is arranged at the front part of the power cabin;
and the driving motor is used for driving the propeller.
Optionally, the propeller is a contra-rotating pitch propeller with an automatic tilter.
Optionally, the unmanned aerial vehicle further comprises an airborne avionics device, wherein the airborne avionics device is used for controlling the operation of the tail-seated vertical take-off and landing solar unmanned aerial vehicle.
The invention provides a tail-sitting type vertical take-off and landing solar unmanned aerial vehicle, which has the beneficial effects that:
1. the unmanned aerial vehicle can not only vertically take off and land without depending on the design of an airport runway through a power structure, but also hover at a fixed point above a target, and can fly for a long distance during long voyage;
2. the unmanned aerial vehicle provides a capacity source by utilizing solar energy, has a storage battery, is long in flight time and long in flight distance, and can greatly expand application capacity;
3. the unmanned aerial vehicle can switch the operation mode through the ailerons and the contra-rotating variable-pitch propellers with the automatic inclinators, does not need a rotating mechanism and a complex control mechanism, has simple structure and convenient operation and control, and is easy to realize the switching of vertical take-off and landing and flight modes;
4. the unmanned aerial vehicle adopts the layout of the flying wings with a large aspect ratio, so that on one hand, the lift-drag ratio is high, and the performance is good when the unmanned aerial vehicle is used as a fixed wing for flying; on the other hand, the undercarriage is arranged at the tail part of the power structure and the tail part of the machine body, and is free of an empennage, so that tail-sitting type parking is facilitated.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
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, in which like reference numerals generally represent like parts throughout.
Fig. 1 is a schematic top view of a tail-seated vertical take-off and landing solar drone according to an embodiment of the present invention.
Fig. 2 is a schematic front view of a tail-seated vertical take-off and landing solar drone according to an embodiment of the present invention.
Fig. 3 is a schematic side view of a flat flight state of a tail-seated vertical take-off and landing solar drone according to an embodiment of the present invention.
Fig. 4 shows a schematic view of a flight process of a tail-seated vertical take-off and landing solar drone according to an embodiment of the invention.
Description of reference numerals:
1. a body; 2. an airfoil; 3. a power structure; 4. a landing gear; 5. an aileron; 6. a solar panel; 7. a storage battery; 8. a power compartment; 9. a propeller; 10. a drive motor; 11. airborne avionics.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, 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.
The invention provides a tail-sitting type vertical take-off and landing solar unmanned aerial vehicle, which comprises:
a body;
the wing is connected with the fuselage, and the wing tip of the wing inclines towards the upper part of the fuselage;
the solar cell panel is arranged on the upper surface of the wing;
the power structure is arranged on the wingtip of the wing;
and the undercarriage is arranged at the tail part of the power structure and the tail part of the airframe.
Specifically, the wings of the unmanned aerial vehicle are provided with an upper reverse structure, and undercarriage are arranged at the tail part of the power structure and the tail part of the body to form a triangular support, so that the unmanned aerial vehicle is stably parked in the taking-off and landing stage, and vertical taking-off and landing can be realized; this unmanned aerial vehicle adopts high photoelectric conversion efficiency's flexible thin-film solar cell panel, and the shop is in the wing upper surface, provides the energy source for unmanned aerial vehicle.
Optionally, the fuselage is a short-cabin fuselage, the wings include a left wing and a right wing that are symmetrical to each other, and the fuselage is disposed right below a symmetrical plane of the left wing and the right wing.
Specifically, the left wing and the right wing are integrated.
Optionally, the wings are in a high aspect ratio all-wing configuration, and the wings are rectangular wings with upper reverse equal chord length.
Specifically, the high-aspect-ratio flying wing layout is adopted, so that on one hand, the lift-drag ratio is high, and the performance is good when the flying wing is used as a fixed wing; on the other hand, the tail wing is not arranged, thus being beneficial to the tail sitting type parking.
Optionally, the trailing edge of the wing is symmetrically provided with two flaps.
Specifically, the ailerons implement partial control of the drone.
Optionally, a storage battery is arranged in the wing, and the storage battery is connected with the solar cell panel and the power structure.
Specifically, two groups of high-energy-density lithium batteries are adopted as storage batteries, are respectively installed inside the wings in a bilateral symmetry mode, store partial electric energy converted by the solar batteries, and provide energy sources for the unmanned aerial vehicle when the solar energy is insufficient in the daytime or at night.
Optionally, the landing gear is a retractable landing gear.
Specifically, when this unmanned aerial vehicle flies with the fixed wing mode, all receive in the short cabin of power structure or fuselage to three frames are in order to reduce the resistance when flying.
Optionally, the power structure comprises:
the power cabin is arranged on the wingtips of the wings;
the propeller is arranged at the front part of the power cabin;
and the driving motor is used for driving the propeller.
Specifically, the two power cabins are respectively positioned at the left wingtip and the right wingtip of the wing and are used for connecting the wing and installing a propeller and a driving motor; the driving motors are two brushless direct current motors which are respectively arranged at the front parts of the two power cabins and drive the propeller to rotate.
Optionally, the propeller is a contra-rotating pitch propeller with an automatic tilter.
Specifically, the propeller is arranged right in front of the two power cabins to provide power for the unmanned aerial vehicle; in one example, the propeller is a two-bladed propeller that has greater efficiency when the drone is flying in fixed-wing mode based on the characteristics of the solar drone that flies for long periods of time.
Optionally, the unmanned aerial vehicle further comprises an airborne avionics device, and the airborne avionics device is used for controlling the operation of the tail-seated vertical take-off and landing solar unmanned aerial vehicle.
Specifically, the airborne avionic device comprises an airborne link, a flight control machine, an inertial navigation device, a steering engine, an energy manager, a device distributor, an electric cable and other devices, and is symmetrically arranged inside the wing as much as possible.
Examples
As shown in fig. 1 to 4, the present invention provides a tail-seated vertical take-off and landing solar drone, comprising:
a body 1;
the wing 2 is connected with the fuselage 1, and the tip end of the wing 2 inclines towards the upper part of the fuselage 1;
the solar cell panel 6 is arranged on the upper surface of the wing 2;
the power structure 3 is arranged on the wingtip of the wing 2;
and the landing gear 4 is arranged at the tail part of the power structure 3 and the tail part of the fuselage 1.
In this embodiment, the fuselage 1 is a nacelle type fuselage, the wings 2 include a left wing and a right wing that are symmetrical to each other, and the fuselage 1 is disposed right below a symmetrical plane of the left wing and the right wing.
In the embodiment, the wing 2 is in a high aspect ratio all-wing configuration, and the wing 2 is a rectangular wing with upper, lower, equal chord length.
In this embodiment, two flaps 5 are symmetrically disposed on the trailing edge of the wing 2.
In this embodiment, the upper surface of the wing 2 is provided with a flexible thin film solar panel.
In the present embodiment, a storage battery 7 is arranged in the wing 2, and the storage battery 7 is connected with the solar panel 6 and the power structure 3.
In the present embodiment, the landing gear 4 is a retractable landing gear.
In the present embodiment, the power structure 3 includes:
the power cabin 8, the power cabin 8 is set up on the wing tip of the wing 2;
the propeller 9 is arranged at the front part of the power cabin 8;
and a driving motor 10 for driving the propeller 9.
In the present embodiment, the propeller 9 is a contra-rotating pitch propeller with an automatic tilter.
In this embodiment, an airborne avionics device 11 is further included, and the airborne avionics device 11 is used for controlling the operation of the tail-seated vertical take-off and landing solar unmanned aerial vehicle.
In conclusion, the tail-sitting type vertical take-off and landing solar unmanned aerial vehicle provided by the invention has the advantages that when the unmanned aerial vehicle takes off, the undercarriage 4 is opened, the airborne avionic equipment 11 gradually coordinates and increases the torque and the rotating speed of the propeller 9, the unmanned aerial vehicle can stably and vertically lift off the ground in a helicopter mode, and then the undercarriage 4 is retracted. After a certain height is reached, the automatic inclinator tilts forward and is matched with the downward deflection of the aileron 5 to generate a head-lowering moment to enable the unmanned aerial vehicle to be in a fixed wing mode flat flight state. When landing, the aircraft climbs to the vertical upward direction of the aircraft nose, then the torque and the rotating speed of the propeller 9 are coordinately reduced, the altitude is slowly reduced until the undercarriage 4 is opened, and then the aircraft stably and vertically lands. When the unmanned aerial vehicle flies in a helicopter mode, pitching control, yawing control and rolling control are respectively realized through synchronous inclination of the automatic inclinator, differential inclination of the automatic inclinator and differential motion of the propeller 9, and vertical lifting, lateral flying and front-back flying control are realized through adjusting the rotating speed and torque of the propeller 9. When the unmanned aerial vehicle flies in a fixed wing mode, pitching control, rolling control and yawing control are realized through synchronous deflection of the ailerons 5, differential deflection of the ailerons 5 and differential deflection of the propellers 9. The energy source is provided by the solar panel 6 and the storage battery 7 in the whole flight process.
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 tail sitting posture VTOL solar energy unmanned aerial vehicle which characterized in that, this unmanned aerial vehicle includes:
a body;
the wing is connected with the fuselage, and the wing tip end of the wing inclines towards the upper part of the fuselage;
the solar cell panel is arranged on the upper surface of the wing;
the power structure is arranged on the wingtip of the wing;
and the undercarriage is arranged at the tail part of the power structure and the tail part of the airframe.
2. The tail-sitting vertical take-off and landing solar unmanned aerial vehicle of claim 1, wherein the fuselage is a short-cabin fuselage, the wings comprise a left wing and a right wing which are symmetrical to each other, and the fuselage is arranged right below the symmetrical plane of the left wing and the right wing.
3. The tail-sitting VTOL solar UAV of claim 1, wherein the wings are in high aspect ratio flyer configuration and the wings are rectangular wings with upper, lower and equal chord length.
4. The tail-sitting vertical take-off and landing solar unmanned aerial vehicle of claim 1, wherein the trailing edge of the wing is symmetrically provided with two flaps.
5. The tail-sitting vertical take-off and landing solar unmanned aerial vehicle of claim 1, wherein the upper surface of the wing is provided with a flexible thin film solar panel.
6. The tail-sitting vertical take-off and landing solar unmanned aerial vehicle of claim 1, wherein a storage battery is disposed in the wing, and the storage battery is connected with the solar panel and the power structure.
7. The tail-seated vertical take-off and landing solar-powered drone of claim 1, wherein the landing gear is a retractable landing gear.
8. The tail-seated vertical take-off and landing solar-powered drone of claim 1, wherein the power structure comprises:
the power cabin is arranged on the wingtips of the wings;
the propeller is arranged at the front part of the power cabin;
and the driving motor is used for driving the propeller.
9. The tail-sitting vertical take-off and landing solar-powered drone of claim 8, wherein the propeller is a contra-rotating pitch propeller with an automatic tilter.
10. The tailback vertical take-off and landing solar-powered drone of claim 1, further comprising an onboard avionics device for controlling operation of the tailback vertical take-off and landing solar-powered drone.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111344745.6A CN113788143A (en) | 2021-11-15 | 2021-11-15 | Tail sitting type vertical take-off and landing solar unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111344745.6A CN113788143A (en) | 2021-11-15 | 2021-11-15 | Tail sitting type vertical take-off and landing solar unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN113788143A true CN113788143A (en) | 2021-12-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111344745.6A Pending CN113788143A (en) | 2021-11-15 | 2021-11-15 | Tail sitting type vertical take-off and landing solar unmanned aerial vehicle |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| US20110233329A1 (en) * | 2010-03-26 | 2011-09-29 | Aerovel Corporation | Method and apparatus for automated launch, retrieval, and servicing of a hovering aircraft |
| CN103287576A (en) * | 2013-05-24 | 2013-09-11 | 北京航空航天大学 | Tailless layout single tail seat type vertical take-off and landing aircraft |
| CN108116656A (en) * | 2017-12-20 | 2018-06-05 | 广东翼景信息科技有限公司 | A kind of solar energy unmanned plane |
| CN109795682A (en) * | 2018-12-10 | 2019-05-24 | 清华大学 | A kind of efficient tail sitting posture VTOL Fixed Wing AirVehicle and its control method |
| CN110466754A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of tailstock formula tilting rotor vertical take-off and landing drone |
| CN211685607U (en) * | 2019-12-16 | 2020-10-16 | 宇领星际航空(苏州)有限公司 | But folding unmanned aerial vehicle of VTOL tail seat |
-
2021
- 2021-11-15 CN CN202111344745.6A patent/CN113788143A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110233329A1 (en) * | 2010-03-26 | 2011-09-29 | Aerovel Corporation | Method and apparatus for automated launch, retrieval, and servicing of a hovering aircraft |
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN103287576A (en) * | 2013-05-24 | 2013-09-11 | 北京航空航天大学 | Tailless layout single tail seat type vertical take-off and landing aircraft |
| CN108116656A (en) * | 2017-12-20 | 2018-06-05 | 广东翼景信息科技有限公司 | A kind of solar energy unmanned plane |
| CN109795682A (en) * | 2018-12-10 | 2019-05-24 | 清华大学 | A kind of efficient tail sitting posture VTOL Fixed Wing AirVehicle and its control method |
| CN110466754A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of tailstock formula tilting rotor vertical take-off and landing drone |
| CN211685607U (en) * | 2019-12-16 | 2020-10-16 | 宇领星际航空(苏州)有限公司 | But folding unmanned aerial vehicle of VTOL tail seat |
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Application publication date: 20211214 |