CN110562452A - Can dismantle VTOL unmanned aerial vehicle of use - Google Patents
Can dismantle VTOL unmanned aerial vehicle of use Download PDFInfo
- Publication number
- CN110562452A CN110562452A CN201910897159.0A CN201910897159A CN110562452A CN 110562452 A CN110562452 A CN 110562452A CN 201910897159 A CN201910897159 A CN 201910897159A CN 110562452 A CN110562452 A CN 110562452A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- wings
- fuselage
- machine body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
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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
- B64C1/069—Joining arrangements therefor
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Platform Screen Doors And Railroad Systems (AREA)
Abstract
The invention provides a detachable vertical take-off and landing unmanned aerial vehicle, which comprises a body, a rotor wing, wings, an empennage and a horizontal power motor, wherein the rotor wing is arranged on the body; the rotor wing is fixed on the machine body by adopting a cross structure; the wings are connected with the fuselage in an inserting manner; the tail wings are spliced at the tail part of the machine body in a clamping manner; the horizontal power motor is arranged at the front end of the machine body. Comprising four rotors. The detachable vertical take-off and landing unmanned aerial vehicle greatly saves the space required by carrying and transporting; after being disassembled, the unmanned plane can be used as a four-rotor unmanned plane to independently work; when long-distance cruise is needed, operation can be carried out according to the combined type vertical take-off and landing unmanned aerial vehicle mode after the unmanned aerial vehicle is assembled.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing unmanned aerial vehicle capable of being detached for use.
Background
Because the vertical take-off and landing unmanned aerial vehicle has the capabilities of vertical take-off and landing and quick maneuvering, the vertical take-off and landing unmanned aerial vehicle is more and more widely applied to the aspects of complex terrain take-off and landing, military reconnaissance, aerial photography and the like. For the VTOL unmanned aerial vehicle, have the characteristics that cruise time is long, take off conveniently, but the existence of its fixed wing makes the occupation amount to the space too big when ground transportation or cluster are put in, has increased the cost of transportation.
Disclosure of Invention
In order to solve the problems, the invention provides a vertical take-off and landing unmanned aerial vehicle capable of being detached for use, which comprises the following components:
A detachable vertical take-off and landing unmanned aerial vehicle is provided, wings are arranged on the unmanned aerial vehicle body and can be detached; the four rotary wings are fixed on the machine body in a cross structure; the tail wing is arranged at the rear part of the fuselage and can be detached; the horizontal power motor is arranged on the machine head.
For easier and more reliable flight, the structure of the drone is as simple as possible.
The utility model provides a can dismantle VTOL unmanned aerial vehicle who uses, two wings are through the tubular structure of a desirable cross fuselage, peg graft in the fuselage both sides.
the utility model provides a can dismantle unmanned aerial vehicle that takes off and land that uses, the fin passes through the mode of joint and fuselage afterbody connection.
The advantages of the invention are as follows:
The detachable vertical take-off and landing unmanned aerial vehicle greatly saves the space required by carrying and transporting; after being disassembled, the unmanned plane can be used as a four-rotor unmanned plane to independently work; when long-distance cruise is needed, operation can be carried out according to the combined type vertical take-off and landing unmanned aerial vehicle mode after the unmanned aerial vehicle is assembled.
Drawings
FIG. 1 is a schematic top view of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the following examples and the accompanying drawings.
As shown in fig. 1, a vertical take-off and landing unmanned aerial vehicle capable of being detached for use comprises a body 1, a rotor 2, wings 3, a tail 4 and a horizontal power motor; the rotor 2 is fixed on the fuselage 1 by adopting a cross structure; the wings 3 are connected with the fuselage 1 in an inserting manner; the tail wing 4 is spliced at the tail part of the machine body 1 in a clamping manner; the horizontal power motor is arranged at the front end of the machine body 1.
Comprising four rotors 2.
Two wings 3 are inserted on both sides of the fuselage 1 through a tubular structure which preferably traverses the fuselage 1.
The utility model provides a can dismantle VTOL unmanned aerial vehicle that uses, wing 3 and fin 4 are dismantling the back, can be independent as 2 unmanned aerial vehicles of a four rotors to carry out independent operation.
The wings 3 can be connected with the fuselage 1 by a splicing method, and the tail wings 4 are connected with the tail part of the fuselage 1 by a clamping method. After the assembly is completed, the aircraft can vertically take off and then is converted into fixed wing flight through simple operation to carry out long-distance operation.
on the basis of the prior art, the detachable vertical take-off and landing unmanned aerial vehicle is more convenient to carry and transport and saves space through modular processing, and the unmanned aerial vehicle can be operated in a multi-rotor 2 mode and a fixed wing mode, so that the unmanned aerial vehicle is fully utilized. The operation is freely changed according to different working environments and operation requirements.
Claims (3)
1. The utility model provides a can dismantle VTOL unmanned aerial vehicle of use which characterized in that: comprises a fuselage, a rotor wing, a wing, an empennage and a horizontal power motor; the rotor wing is fixed on the machine body by adopting a cross structure; the wings are connected with the fuselage in an inserting manner; the tail wings are spliced at the tail part of the machine body in a clamping manner; the horizontal power motor is arranged at the front end of the machine body.
2. The detachable VTOL UAV of claim 1, wherein: comprising four rotors.
3. The detachable VTOL UAV of claim 1, wherein: the two wings are inserted on the two sides of the fuselage through a tubular structure which preferably traverses the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910897159.0A CN110562452A (en) | 2019-09-23 | 2019-09-23 | Can dismantle VTOL unmanned aerial vehicle of use |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910897159.0A CN110562452A (en) | 2019-09-23 | 2019-09-23 | Can dismantle VTOL unmanned aerial vehicle of use |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110562452A true CN110562452A (en) | 2019-12-13 |
Family
ID=68781760
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910897159.0A Pending CN110562452A (en) | 2019-09-23 | 2019-09-23 | Can dismantle VTOL unmanned aerial vehicle of use |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110562452A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115924070A (en) * | 2022-11-28 | 2023-04-07 | 西北工业大学 | Barrel type launching and spreading foldable single-control-plane aircraft and design method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691736A (en) * | 2015-03-12 | 2015-06-10 | 江苏艾锐泰克无人飞行器科技有限公司 | Fixed-wing unmanned aerial vehicle |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| CN205770149U (en) * | 2016-05-24 | 2016-12-07 | 中电科（德阳广汉）特种飞机系统工程有限公司 | A kind of fixed-wing rotor mixing unmanned plane of multi-configuration |
| CN206954505U (en) * | 2016-08-26 | 2018-02-02 | 西安融智航空科技有限公司 | One kind is tethered at cruise multi-mode VUAV |
| CN109733599A (en) * | 2019-02-27 | 2019-05-10 | 广西翼界科技有限公司 | A kind of combined dual-purpose unmanned plane |
-
2019
- 2019-09-23 CN CN201910897159.0A patent/CN110562452A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| CN104691736A (en) * | 2015-03-12 | 2015-06-10 | 江苏艾锐泰克无人飞行器科技有限公司 | Fixed-wing unmanned aerial vehicle |
| CN205770149U (en) * | 2016-05-24 | 2016-12-07 | 中电科（德阳广汉）特种飞机系统工程有限公司 | A kind of fixed-wing rotor mixing unmanned plane of multi-configuration |
| CN206954505U (en) * | 2016-08-26 | 2018-02-02 | 西安融智航空科技有限公司 | One kind is tethered at cruise multi-mode VUAV |
| CN109733599A (en) * | 2019-02-27 | 2019-05-10 | 广西翼界科技有限公司 | A kind of combined dual-purpose unmanned plane |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115924070A (en) * | 2022-11-28 | 2023-04-07 | 西北工业大学 | Barrel type launching and spreading foldable single-control-plane aircraft and design method thereof |
| CN115924070B (en) * | 2022-11-28 | 2023-08-11 | 西北工业大学 | Barrel type launching and scattering foldable single-control-surface aircraft and design method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191213 |