CN108284949B - Foldable staggered six-rotor aircraft - Google Patents
Foldable staggered six-rotor aircraft Download PDFInfo
- Publication number
- CN108284949B CN108284949B CN201810177802.8A CN201810177802A CN108284949B CN 108284949 B CN108284949 B CN 108284949B CN 201810177802 A CN201810177802 A CN 201810177802A CN 108284949 B CN108284949 B CN 108284949B
- Authority
- CN
- China
- Prior art keywords
- rotor
- rotor wing
- machine body
- foldable
- support arm
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- 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.)
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Links
- 238000009434 installation Methods 0.000 claims abstract description 10
- 230000007246 mechanism Effects 0.000 claims abstract description 7
- 230000000694 effects Effects 0.000 abstract description 5
- 238000005507 spraying Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 239000003814 drug Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000000575 pesticide Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- 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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
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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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Pest Control & Pesticides (AREA)
- Toys (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention discloses a foldable staggered six-rotor aircraft, which comprises a fuselage, rotor support arms, a motor, rotors and landing gears. The fuselage is box structure, and six rotor support arms divide into two sets of through folding mechanism installation in fuselage both sides equally. The motor installation direction on the front support arm and the rear support arm in each group of support arms is the same, and the motor on the support arm at the middle position is opposite to the motor installation direction on the front support arm and the rear support arm. When the foldable rotor is fully opened, the rotor at the middle position of each side of the fuselage overlaps with the front rotor and the rear rotor by less than 25% of the area of the single rotor. The two landing gears are symmetrically fixedly connected on the front side and the rear side below the side of the machine body. The foldable rotor wing supporting arm is adopted in the scheme of the invention, so that the aircraft has smaller volume in a non-working state, and is convenient to transport, carry and store; the calculated overlapping range of the staggered rotor wings is optimized, so that the aircraft has smaller volume in the working state, and meanwhile, a good spraying effect is obtained and the flight safety is improved.
Description
Technical Field
The invention relates to the field of multi-rotor aircraft, in particular to a foldable staggered six-rotor aircraft.
Background
The six-rotor aircraft has the advantages of large load, simple structure, stable flight, easy operation and the like, is very suitable for executing middle-short distance flight tasks, and is more and more widely used in the fields of aerial photography, inspection, plant protection and the like.
The rotor wings of the existing six-rotor aircraft are generally symmetrically and uniformly distributed around the fuselage, and most of the rotor wings are rotor wing supporting arms fixedly connected with the fuselage, so that the six-rotor aircraft is large in size and inconvenient to store and transport. The existing foldable six-rotor aircraft is small in size when in a folded state, and the rotor support arm is in a completely opened state when in a working state, so that the size of the existing foldable six-rotor aircraft is also large. While an aircraft for the field of plant protection needs to have a small volume for storage and transportation in a non-working state, and a large weight due to a load in a working state, at this time, needs to have a small volume for operation such as single person carrying, it is difficult for a fixed six-rotor aircraft and a foldable six-rotor aircraft in the prior art to meet the requirement.
A many rotor crafts for plant protection need consider down the influence effect of gas flow to the atomizing liquid medicine that sprays, and conventional non-crisscross many rotor crafts down gas flow not concentrate enough at work, can lead to the scattering everywhere when vaporific liquid medicine sprays, seriously influences the plant protection effect. At this time, the flying height needs to be reduced to improve the spraying effect, so that hidden danger in the aspect of flying safety is brought.
Disclosure of Invention
The object of the present invention is to overcome the above problems by providing a foldable staggered six-rotor aircraft.
In order to achieve the above purpose, the method adopted by the invention is as follows: comprises a machine body, a rotor wing supporting arm, a motor, a rotor wing and a landing gear. The method is characterized in that: the body is of a box structure, a power supply is installed in the body, six rotor wing supporting arms are installed on two sides of the body, two landing gears are installed below the body, and a load space is reserved between the lower side of the body and the landing gears. The six rotor wing supporting arms are equally divided into two groups and are arranged on the left side and the right side of the machine body, and the six rotor wing supporting arms are connected with the machine body through folding mechanisms. The motor is arranged at the far machine body end of the rotor wing supporting arm, the motor installation directions of the front supporting arm and the rear supporting arm in each group of supporting arms are the same up and down, and the motor on the supporting arm at the middle position is opposite to the motor installation directions of the front supporting arm and the rear supporting arm up and down. The rotor wing is a foldable rotor wing and is arranged on an output shaft of the motor. When the rotor wing is completely opened in the working state, in the overlook state, the rotor wing at the middle position of each side of the fuselage and the front rotor wing and the rear rotor wing have the overlapping of less than 25% of the area range of the single rotor wing. The two landing gears are symmetrically and fixedly arranged at the front side and the rear side below the side of the machine body.
Preferably, the rotor support arm is locked in parallel with the fuselage in the operating state, and is foldable to a position perpendicular to the fuselage by a folding mechanism in the non-operating state.
Preferably, the foldable rotor wing is of a three-section structure, is unfolded into a straight shape along the diameter direction of the rotor face disc in the working state, and can be folded around the root hub in the non-working state.
Preferably, the landing gear is of a ladder-shaped structure with a narrow upper part and a wide lower part, and a cross beam for carrying operation is arranged on the landing gear.
The beneficial effects are that:
compared with the traditional scheme, the technical scheme of the invention adopts the folding and unfolding of the foldable rotor wing supporting arm, so that the aircraft can normally fly in a working state, and has higher flying efficiency; the device has small size and light weight in the non-working state, is convenient to transport, carry and store, and can carry more effective loads under the same size. In addition, the scheme also adopts a staggered and overlapped rotor wing scheme, so that the aircraft has smaller volume in the working state on one hand, and is convenient for a single person to operate; on the other hand, through optimizing the staggered overlapping range of less than 25% single rotor area that calculates, reduce the volume of aircraft under operating condition in the at utmost, reduce the mutual interference of air current between the rotor as far as possible, still make down wash the air current more concentrated, the directionality is good, the coverage is big and be difficult for receiving the crosswind influence, the atomizing pesticide that sprays out follows the air current motion, can obtain better spraying effect, the aircraft can be at higher flight altitude operation in addition, avoid the risk of low altitude collision.
Drawings
FIG. 1 is a schematic view of a foldable interleaved six-rotor aircraft in an operational state;
FIG. 2 is a top view of a foldable interleaved six-rotor aircraft in an operational state;
FIG. 3 is a schematic view of a foldable interleaved six-rotor aircraft in a non-operational state.
Shown in fig. 1 to 3 are 1, fuselage, 2, rotor support arms, 3, motor, 4, rotor, 5, landing gear.
Detailed Description
The invention will be further illustrated by the following drawings and specific examples, which are carried out on the basis of the technical solutions of the invention, it being understood that these examples are only intended to illustrate the invention and are not intended to limit the scope of the invention.
Example 1:
fig. 1 is a schematic view of an operating state of the foldable staggered six-rotor aircraft, and fig. 2 is a top view of an operating state of the foldable staggered six-rotor aircraft. The embodiment discloses a foldable staggered six-rotor aircraft, which comprises a fuselage 1, rotor support arms 2, motors 3, rotors 4 and landing gear 5. The method is characterized in that: the machine body 1 is of a box structure, a power supply is installed in the machine body, six rotor wing supporting arms 2 are installed on two sides of the machine body, two landing gears 5 are installed below the machine body, and a load space is reserved between the lower side of the machine body and the landing gears 5. The six rotor wing support arms 2 are equally divided into two groups and are arranged on the left side and the right side of the machine body 1, and are connected with the machine body 1 through folding mechanisms. The motor 3 is arranged at the far machine body end of the rotor wing supporting arm 2, the installation directions of the motor 3 on the front supporting arm 2 and the rear supporting arm 2 in each group of supporting arms 2 are the same up and down, and the installation directions of the motor 3 on the middle supporting arm 2 are opposite up and down to the installation directions of the motor 3 on the front supporting arm 2 and the rear supporting arm 2. The rotor 4 is a foldable rotor and is arranged on the output shaft of the motor 3. When the rotor 4 is fully opened in the working state, in the top view state, the rotor 4 at the middle position of each side of the fuselage 1 and the front and rear rotors 4 have an overlapping of less than 25% of the area range of the single rotor 4. The two landing gears 5 are symmetrically and fixedly arranged at the front side and the rear side below the side of the machine body 1.
As shown in fig. 3, the foldable staggered six-rotor aircraft is schematically shown in a non-working state, the rotor support arms 2 are locked in parallel with the fuselage 1 in the working state, and can be folded to a position perpendicular to the fuselage 1 by a folding mechanism in the non-working state.
As shown in fig. 1 to 3, the rotor 4 is of a three-section foldable structure, and is unfolded in a working state to be a straight line in the diameter direction of a rotor disc, and is folded around a root hub in a non-working state.
The landing gear 5 is a ladder-like structure with a narrow upper part and a wide lower part, and is provided with a cross beam for carrying operation, as shown in fig. 1 to 3.
The technical means disclosed by the scheme of the invention is not limited to the technical means disclosed by the technical means, and also comprises the technical scheme formed by any combination of the technical features. While the foregoing is directed to embodiments of the present invention, it will be appreciated by those skilled in the art that changes and modifications may be made without departing from the principles of the invention, and such changes and modifications are intended to be included within the scope of the invention.
Claims (4)
1. The utility model provides a six rotor crafts of collapsible crisscross, includes fuselage, rotor support arm, motor, rotor, undercarriage, its characterized in that: the machine body is of a box structure, a power supply is arranged in the machine body, six rotor wing supporting arms are arranged on two sides of the machine body, two landing gears are arranged below the machine body, a load space is reserved between the lower side of the machine body and the landing gears, and the six rotor wing supporting arms are equally divided into two groups and are arranged on the left side and the right side of the machine body and are connected with the machine body through a folding mechanism; the motors are arranged at the far machine body end of the rotor wing support arms, the motor installation directions of the front rotor wing support arm and the rear rotor wing support arm in each group of rotor wing support arms are the same up and down, and the motor on the rotor wing support arm at the middle position is opposite to the motor installation directions of the front rotor wing support arm and the rear rotor wing support arm up and down; the rotor wing is a foldable rotor wing, the rotor wing is arranged on an output shaft of the motor, when the rotor wing is completely opened in a working state, in a overlook state, the rotor wing at the middle position of each side edge of the machine body and the front rotor wing and the rear rotor wing are overlapped within the area range of less than 25% of a single rotor wing, and the two landing gears are symmetrically and fixedly arranged on the front side and the rear side below the machine body.
2. A foldable interleaved six rotor aircraft according to claim 1 wherein: the rotor wing supporting arm is locked with the machine body in parallel in the working state, and can be folded to a position vertical to the machine body through the folding mechanism in the non-working state.
3. A foldable interleaved six rotor aircraft according to claim 1 or 2 wherein: the foldable rotor wing is of a three-section structure, is unfolded to be in a straight shape in the diameter direction of the rotor face disc in a working state, and can be folded around the root hub in a non-working state.
4. A foldable interleaved six rotor aircraft according to claim 1 or 2 wherein: the landing gear is of a ladder-shaped structure with a narrow upper part and a wide lower part, and a cross beam for carrying operation is arranged on the landing gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810177802.8A CN108284949B (en) | 2018-03-05 | 2018-03-05 | Foldable staggered six-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810177802.8A CN108284949B (en) | 2018-03-05 | 2018-03-05 | Foldable staggered six-rotor aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108284949A CN108284949A (en) | 2018-07-17 |
| CN108284949B true CN108284949B (en) | 2023-09-08 |
Family
ID=62833296
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810177802.8A Active CN108284949B (en) | 2018-03-05 | 2018-03-05 | Foldable staggered six-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108284949B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661327B (en) * | 2019-03-05 | 2023-04-07 | 上海科技大学 | Many rotors of flexible fuselage flight device |
| JP7384337B2 (en) * | 2019-07-24 | 2023-11-21 | イームズロボティクス株式会社 | Unmanned flying vehicle with improved quietness |
| CN111498097B (en) * | 2020-05-06 | 2021-07-16 | 中航金城无人系统有限公司 | Six rotor unmanned aerial vehicle |
| CN112549886A (en) * | 2020-12-25 | 2021-03-26 | 南京航空航天大学 | Amphibious six-rotor aircraft applicable to multiple terrains and having walking function |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204395444U (en) * | 2014-11-25 | 2015-06-17 | 昆山优力电能运动科技有限公司 | Collapsible multi-rotor aerocraft |
| CN205819568U (en) * | 2016-07-04 | 2016-12-21 | 广东天米教育科技有限公司 | A kind of many rotors heavy－duty plant protection unmanned plane |
| CN106394858A (en) * | 2016-12-08 | 2017-02-15 | 天津中翔腾航科技股份有限公司 | Folded six-rotor unmanned plane |
| CN206704547U (en) * | 2017-05-11 | 2017-12-05 | 深圳市九天创新科技有限责任公司 | A kind of rotary nozzle folds plant protection unmanned plane |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100044499A1 (en) * | 2008-08-22 | 2010-02-25 | Draganfly Innovations Inc. | Six rotor helicopter |
-
2018
- 2018-03-05 CN CN201810177802.8A patent/CN108284949B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204395444U (en) * | 2014-11-25 | 2015-06-17 | 昆山优力电能运动科技有限公司 | Collapsible multi-rotor aerocraft |
| CN205819568U (en) * | 2016-07-04 | 2016-12-21 | 广东天米教育科技有限公司 | A kind of many rotors heavy－duty plant protection unmanned plane |
| CN106394858A (en) * | 2016-12-08 | 2017-02-15 | 天津中翔腾航科技股份有限公司 | Folded six-rotor unmanned plane |
| CN206704547U (en) * | 2017-05-11 | 2017-12-05 | 深圳市九天创新科技有限责任公司 | A kind of rotary nozzle folds plant protection unmanned plane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108284949A (en) | 2018-07-17 |
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