CN108284949A - A kind of foldable staggeredly six rotorcraft - Google Patents
A kind of foldable staggeredly six rotorcraft Download PDFInfo
- Publication number
- CN108284949A CN108284949A CN201810177802.8A CN201810177802A CN108284949A CN 108284949 A CN108284949 A CN 108284949A CN 201810177802 A CN201810177802 A CN 201810177802A CN 108284949 A CN108284949 A CN 108284949A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- rotor
- foldable
- motor
- support arm
- 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.)
- Granted
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Classifications
-
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
Abstract
The invention discloses a kind of foldable staggeredly six rotorcrafts, including fuselage, flight support arm, motor, rotor, undercarriage.Fuselage is body structure, and six flight support arms are divided into two groups and are mounted on fuselage both sides by fold mechanism.Motor installation direction in every group of support arm on front and back two support arms is identical, and the motor on support arm in an intermediate position is opposite with the motor installation direction on front and back two support arms.In complete open, rotor of the fuselage per side centre position has overlapping less than 25% single rotor areal extent foldable rotor with former and later two rotors.Two undercarriages are symmetrically fixed in the front and rear sides of fuselage side-lower.The present invention program uses foldable flight support arm, so that aircraft is had smaller size smaller in off working state, is readily transported, carries and stores；By optimizing calculated staggeredly rotor overlapping range, make aircraft that also there is smaller volume in working condition, while obtaining good spray effect and improving flight safety.
Description
Technical field
The present invention relates to multi-rotor aerocraft field, more particularly to a kind of foldable staggeredly six rotorcraft.
Background technology
Six rotorcraft has many advantages, such as big load-carrying, simple in structure, flight stability and easily operated, is very suitable for holding
The aerial mission of row short-distance and medium-distance is more widely deployed for taking photo by plane, works, the agriculture field such as inspection and plant protection.
The rotor of existing six rotorcraft is usually symmetrically and evenly distributed in fuselage surrounding, and the overwhelming majority uses and machine
The flight support arm that body is fixedly connected, volume is larger, is not easy to very much store and transport.Existing foldable six rotorcraft
Its small volume in folded state, in working condition, flight support arm is in completely open state, and volume is also larger.
And be used for the aircraft in plant protection field and not only need that there is smaller volume in off working state in order to store and transport,
Working condition needs it to have smaller volume in order to single carrying etc. at this time due to having larger weight in the presence of load
Operation, fixed six rotorcraft in the prior art and foldable six rotorcraft are difficult to meet the requirement.
Multi-rotor aerocraft for plant protection needs the influence for considering downwash flow to the atomization liquid sprayed, often
The noninterlace multi-rotor aerocraft of rule at work not enough concentrate by downwash flow, can cause to disperse everywhere when misty medicine liquid spray,
Seriously affect plant protection effect.Needing at this time, which reduces flying height, carries out operation to improve spray effect, can bring flight again in this way
The hidden danger of secure context.
Invention content
The purpose of the invention is to overcome the above problem, a kind of foldable staggeredly six rotorcraft is provided.
In order to achieve the above objectives, the method that the present invention uses is：Including fuselage, flight support arm, motor, rotor, rise and fall
Frame.It is characterized in that：The fuselage is body structure, and inside installation electrical source of power, six flight support arms, side are installed in both sides
Two undercarriages are installed in lower section, and there are load spaces between undercarriage below.Six flight support arms, are divided into
Two groups of left and right sides for being mounted on the fuselage, are connect by fold mechanism with the fuselage.The motor is mounted on described
The remote fuselage end of flight support arm, and it is identical above and below the motor installation direction in every group of support arm on front and back two support arms, and
Motor on support arm in an intermediate position and the motor installation direction on front and back two support arms are opposite up and down.The rotor
For foldable rotor, it is mounted on the output shaft of motor.The rotor is when working condition is opened completely, in vertical view state,
Rotor of the fuselage per side centre position has overlapping less than 25% single rotor areal extent with former and later two rotors.It is described
Two undercarriages be symmetrically fixedly mounted on the front and rear sides of the fuselage side-lower.
As a preference of the present invention, the flight support arm is in working condition locking parallel with fuselage, in inoperative shape
State can be folded to and fuselage upright position by fold mechanism.
As a preference of the present invention, the foldable rotor is three stage structure, rotor face is opened in working condition
The linear type in disk diameter direction can be folded in off working state around root propeller hub.
As a preference of the present invention, the undercarriage is up-narrow and down-wide ladder configuration, which is provided with for portable behaviour
The crossbeam of work.
Advantageous effect：
Technical solution of the present invention compares traditional scheme, the opening using foldable flight support arm and folding, makes aircraft in work
Make state and carry out normal flight operation, while also there is higher flight efficiency；In off working state, size is small, light-weight,
It is readily transported, carries and stores, with more payload can be carried under size.In addition, what this programme also use was overlapping
On the one hand rotor scheme makes aircraft also have smaller volume in working condition, be convenient for one man operation；On the other hand by excellent
Change the calculated range that is overlapping for being less than 25% single rotor area, reduces aircraft under working condition to the full extent
Volume, air-flow interferes with each other between reducing rotor as far as possible, so that the downwash flow is more concentrated, good directionality, coverage area it is big
And be not easy to be influenced by crosswind, the atomization pesticide sprayed complies with air motion, can obtain better spray effect, fly in addition
Device can avoid the risk of low latitude collision in higher flying height operation.
Description of the drawings
Fig. 1 is foldable staggeredly six rotorcraft working state schematic representation；
Fig. 2 is foldable staggeredly six rotorcraft working condition vertical view；
Fig. 3 is foldable staggeredly six rotorcraft off working state schematic diagram.
Shown in Fig. 1 to Fig. 3,1, fuselage, 2, flight support arm, 3, motor, 4, rotor, 5, undercarriage.
Specific implementation mode
In the following with reference to the drawings and specific embodiments, the present invention is furture elucidated, and the present embodiment is with technical solution of the present invention
Premised under implemented, it should be understood that these examples are only for illustrating the present invention and are not intended to limit the scope of the present invention.
Embodiment 1：
It is foldable staggeredly six rotorcraft working state schematic representation as shown in Figure 1, Fig. 2 show foldable staggeredly six rotors
Aircraft working condition vertical view.A kind of foldable staggeredly six rotorcraft, including fuselage 1, rotor disclosed in the present embodiment
Support arm 2, motor 3, rotor 4, undercarriage 5.It is characterized in that：The fuselage 1 is body structure, inside installation power electric
Six flight support arms 2 are installed in source, both sides, and side-lower installs two undercarriages 5, and there are load between undercarriage 5 below
Space.Six flight support arms 2, be divided into two groups be mounted on the fuselage 1 the left and right sides, by fold mechanism with
The fuselage 1 connects.The motor 3 is mounted on the remote fuselage end of the flight support arm 2, and front and back in every group of support arm 2
It is identical above and below 3 installation direction of motor on two support arms 2, and the motor 3 on support arm in an intermediate position 2 and front and back two
3 installation direction of motor on support arm 2 is opposite up and down.The rotor 4 is foldable rotor, is mounted on the output shaft of motor 3
On.The rotor 4 is when working condition is opened completely, in vertical view state, rotor 4 of the fuselage 1 per side centre position
Have with former and later two rotors 4 overlapping less than 25% single rotor, 4 areal extent.Two undercarriages 5 are symmetrically fixedly mounted
In the front and rear sides of 1 side-lower of the fuselage.
Foldable staggeredly six rotorcraft off working state schematic diagram, the flight support arm 2 is illustrated in figure 3 to exist
Working condition locking parallel with fuselage 1 can be folded to and 1 upright position of fuselage in off working state by fold mechanism.
Foldable staggeredly six rotorcraft as shown in Figure 1 to Figure 3, the rotor 4 is three-stage folding structure,
It is opened for the linear type in rotor face disk diameter direction in working condition, can be folded around root propeller hub in off working state.
Foldable staggeredly six rotorcraft as shown in Figure 1 to Figure 3, the undercarriage 5 is up-narrow and down-wide scalariform
Structure which is provided with the crossbeam for palm top.
The technical means disclosed in the embodiments of the present invention is not limited to the technical means disclosed in the above technical means, and further includes
By the above technical characteristic arbitrarily the formed technical solution of combination.The above is the specific implementation mode of the present invention, should be referred to
Go out, for those skilled in the art, without departing from the principle of the present invention, can also make several
Improvements and modifications, these improvements and modifications are also considered as protection scope of the present invention.
Claims (4)
1. a kind of foldable staggeredly six rotorcraft, including fuselage, flight support arm, motor, rotor, undercarriage, feature
It is：The fuselage is body structure, and inside installation electrical source of power, six flight support arms, side-lower installation are installed in both sides
Two undercarriages, there are load spaces, described six flight support arms to be divided into two groups of installations between undercarriage below
In the left and right sides of the fuselage, it is connect with the fuselage by fold mechanism；The motor is mounted on the flight support
The remote fuselage end of arm, and it is identical above and below the motor installation direction in every group of support arm on front and back two support arms, and in centre
Motor on the support arm of position and the motor installation direction on front and back two support arms are opposite up and down；The rotor is foldable
Rotor is mounted on the output shaft of motor, and the rotor is when working condition is opened completely, in vertical view state, the fuselage
Rotor per side centre position has overlapping less than 25% single rotor areal extent, described two to rise with former and later two rotors
Fall the front and rear sides that frame is symmetrically fixedly mounted on the fuselage side-lower.
2. the foldable staggeredly six rotorcraft of one kind according to claim 1, it is characterised in that：The flight support
Arm can be folded to and fuselage upright position in working condition locking parallel with fuselage in off working state by fold mechanism.
3. the foldable staggeredly six rotorcraft of one kind according to claim 1 or 2, it is characterised in that：Described rolls over
Folded rotor is three stage structure, and the linear type in rotor face disk diameter direction is opened in working condition, off working state can
Around root, propeller hub is folded.
4. the foldable staggeredly six rotorcraft of one kind as claimed in any of claims 1 to 3, it is characterised in that：
The undercarriage is up-narrow and down-wide ladder configuration, which is provided with the crossbeam for palm top.
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 true CN108284949A (en) | 2018-07-17 |
| CN108284949B 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) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111498097A (en) * | 2020-05-06 | 2020-08-07 | 中航金城无人系统有限公司 | Six rotor unmanned aerial vehicle |
| CN111661327A (en) * | 2019-03-05 | 2020-09-15 | 上海科技大学 | Many rotors of flexible fuselage flight device |
| 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 |
| 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100044499A1 (en) * | 2008-08-22 | 2010-02-25 | Draganfly Innovations Inc. | Six rotor helicopter |
| 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 |
-
2018
- 2018-03-05 CN CN201810177802.8A patent/CN108284949B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100044499A1 (en) * | 2008-08-22 | 2010-02-25 | Draganfly Innovations Inc. | Six rotor helicopter |
| 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 |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661327A (en) * | 2019-03-05 | 2020-09-15 | 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 |
| CN111498097A (en) * | 2020-05-06 | 2020-08-07 | 中航金城无人系统有限公司 | Six rotor unmanned aerial vehicle |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108284949B (en) | 2023-09-08 |
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