CN108791854A - Fold unmanned plane - Google Patents
Fold unmanned plane Download PDFInfo
- Publication number
- CN108791854A CN108791854A CN201810619910.6A CN201810619910A CN108791854A CN 108791854 A CN108791854 A CN 108791854A CN 201810619910 A CN201810619910 A CN 201810619910A CN 108791854 A CN108791854 A CN 108791854A
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- China
- Prior art keywords
- wing
- main wing
- cabin
- aileron
- main
- 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.)
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- 230000008878 coupling Effects 0.000 claims abstract description 3
- 238000010168 coupling process Methods 0.000 claims abstract description 3
- 238000005859 coupling reaction Methods 0.000 claims abstract description 3
- 239000004033 plastic Substances 0.000 claims description 3
- 229920003023 plastic Polymers 0.000 claims description 3
- 230000007306 turnover Effects 0.000 claims description 3
- 108010066057 cabin-1 Proteins 0.000 description 17
- 230000006378 damage Effects 0.000 description 6
- 239000011435 rock Substances 0.000 description 4
- 238000003860 storage Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 230000009977 dual effect Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000007790 scraping Methods 0.000 description 2
- 230000001934 delay Effects 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000002441 reversible effect Effects 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/37—Rotors having articulated joints
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of folding unmanned plane, host wing one end is fixed on the lateral wall of cabin, and the other end extends outwardly along the radial direction of cabin, and the quantity of host wing is for three and uniformly distributed along circumferential direction；Host wing diameter is gradually reduced from inside to outside, end is rotationally hinged with slave wing one end, host wing and the slave wing can coaxially be fixed by fastening bolt, the slave wing other end is equipped with two leaf flight paddles, and the top of undercarriage is mounted on the bottom end of cabin turnablely.Position part outwardly convex on cabin outer wall close to host wing is formed with clamping limb, and clamping limb head is provided with clamping snatch, and when slave wingfold is to close to host wing, the coupling part between the slave wing and flight paddle can be buckled and be fixed by clamping snatch.Its is simple in structure, easy to operate, can when not in use quickly stablize wing and flight paddle and fold, prevent from loosening, reduce overall volume, save operating space.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a folding unmanned aerial vehicle.
Background
Along with more and more folding unmanned aerial vehicle, model aeroplane and model ship, the aircraft of taking photo by plane is applied to civilian field, and because function and lift limit voyage's continuous increase, unmanned aerial vehicle self weight and volume are also continuously increasing to, folding unmanned aerial vehicle after the use is when depositing, and its wing and flight oar that stretch out for a long time can occupy very big space, is very unfavorable for operating space's saving, delays debugging or maintenance efficiency.
Therefore, it is urgently needed to provide a folding unmanned aerial vehicle which is simple in structure and can save occupied space.
Disclosure of Invention
The invention aims to provide a folding unmanned aerial vehicle which is simple in structure and convenient to operate, wings and flight paddles can be stably folded quickly and quickly when the folding unmanned aerial vehicle is not used, looseness is prevented, the overall size is reduced, and the operation space is saved.
In order to achieve the above object, the present invention provides a folding unmanned aerial vehicle, comprising a nacelle, a main wing, an auxiliary wing, and a landing gear; wherein,
one end of each main wing is fixedly connected to the outer side wall of the engine room, the other end of each main wing extends outwards along the radial direction of the engine room, and the number of the main wings is three and the main wings are uniformly distributed along the circumferential direction;
the diameter of the main wing is gradually reduced from inside to outside, the tail end of the main wing is rotatably hinged with one end of the auxiliary wing, the main wing and the auxiliary wing can be coaxially fixed through a fastening bolt, and the other end of the auxiliary wing is provided with a flying paddle which is a two-blade flying paddle;
the top end of the landing gear is arranged at the bottom end of the cabin in a turnable manner, and the landing gear can be accommodated into or extended out of the bottom area of the cabin through turning;
the outer wall of the cabin is provided with a clamping arm which protrudes outwards and is close to the main wing, the head of the clamping arm is provided with a clamping buckle, and when the auxiliary wing is folded to be close to the main wing, the clamping buckle can be used for fixing the buckle of the connecting part between the auxiliary wing and the flying oar.
Preferably, the main wing and/or the auxiliary wing are made of plastic.
Preferably, the connection between the main wing and the auxiliary wing is a detachable connection.
Preferably, the detachable connection is a threaded connection, the main wing and the auxiliary wing are both provided with internal thread holes, the auxiliary wing can be fixed to be coaxial with the main wing by sequentially penetrating through the internal thread holes through bolts, or the auxiliary wing can rotate around the connection part to be close to the cabin by loosening the bolts.
Preferably, the outer wall of the nacelle is provided with crash strips in the areas close to the ailerons.
Preferably, the bumper strip is a sponge strip.
Preferably, a rubber pad is laid on the landing gear in the area contacting the landing surface.
According to the technical scheme, one end of each main wing is fixedly connected to the outer side wall of the cabin, the other end of each main wing extends outwards along the radial direction of the cabin, and the three main wings are uniformly distributed along the circumferential direction, so that the whole folding unmanned aerial vehicle can keep balance all the time in the flying process and stably fly. Meanwhile, the diameter of the main wing is gradually reduced from inside to outside, so that the mechanical strength of the main wing is improved; the tail end of the main wing is rotatably hinged with one end of the auxiliary wing, the main wing and the auxiliary wing can be coaxially fixed through the fastening bolt, and the other end of the auxiliary wing is provided with a flying paddle which is a two-blade flying paddle. The design can realize that after the fastening bolt is loosened, the aileron is rotated to form a complete linear wing coaxial with the main wing, and then the fastening bolt is screwed again for fixing for flying; when the aircraft needs to be stored after flying, the fastening bolt is loosened again, the auxiliary wing rotates towards the cabin direction to enable the auxiliary wing to be attached to the cabin wall, and then the fastening bolt is screwed to fix the auxiliary wing in a storage state. The flight oar is a two-blade flight oar, and can be adjusted to be in a coaxial linear state with the auxiliary wing in a rotating mode, so that the occupied space of the flight oar in an optional state is greatly reduced. The top end of the undercarriage is arranged at the bottom end of the cabin in a turnable manner, and the undercarriage can be stored in the bottom area of the cabin or extend out of the bottom area of the cabin through turning, so that the size of the whole folding unmanned aerial vehicle can be further reduced, the operation space for debugging or maintenance of an operator is saved, the fatigue is reduced, and the good working state of the undercarriage can be kept for a longer time.
Simultaneously, after the aileron is folded and is close to the main wing, in transport or transportation, in case unmanned aerial vehicle's cabin frequently takes place to rock and makes the unexpected not hard up of fastening bolt, can lead to originally fixed folding state between aileron and the main wing to destroy and rock along with external force, not only expand again and occupy great storage space, and the unexpected expansion of aileron can make it receive external force to damage in addition, seriously shortens life. Therefore, a clamping arm is formed at the position part, close to the main wing, on the outer wall of the cabin in an outward protruding mode, the head of the clamping arm is provided with a clamping buckle, and when the auxiliary wing is folded to be close to the main wing, the clamping buckle can be used for fixing the connecting part between the auxiliary wing and the flight oar in a buckling mode. So can form the binding power of dual fail-safe, effectively prevent the destruction of aileron and main wing fixed state, improve the structural stability after unmanned aerial vehicle folds greatly.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic structural diagram of a folding drone according to an embodiment of the present invention.
Description of the reference numerals
1-nacelle 2-main wing
3-aileron 4-undercarriage
5-flight oar 6-clamping arm
7-clamping clasp
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present invention, are given by way of illustration and explanation only, not limitation.
In the present invention, unless otherwise specified, the directional words "inner, outer, top, bottom" and the like included in a term merely represent the orientation of the term in a conventional use state or a colloquial meaning understood by those skilled in the art, and should not be construed as limiting the term.
Referring to fig. 1, the present invention provides a folding drone comprising a nacelle 1, a main wing 2, an auxiliary wing 3 and a landing gear 4; wherein,
one end of each main wing 2 is fixedly connected to the outer side wall of the engine room 1, the other end of each main wing extends outwards along the radial direction of the engine room 1, and the number of the main wings 2 is three and is uniformly distributed along the circumferential direction;
the diameter of the main wing 2 is gradually reduced from inside to outside, the tail end of the main wing 2 is rotatably hinged with one end of the auxiliary wing 3, the main wing 2 and the auxiliary wing 3 can be coaxially fixed through a fastening bolt, the other end of the auxiliary wing 3 is provided with a flying oar 5, and the flying oar 5 is a two-blade flying oar;
the top end of the landing gear 4 is arranged at the bottom end of the cabin 1 in a reversible manner, and the landing gear 4 can be retracted into the bottom area of the cabin 1 or extended out of the bottom area of the cabin 1 through the turnover;
the outer wall of the cabin 1 is provided with a clamping arm 6 protruding outwards at a position close to the main wing 2, the head of the clamping arm 6 is provided with a clamping buckle 7, and when the auxiliary wing 3 is folded to be close to the main wing 2, the clamping buckle 7 can be used for fixing a buckle of a connecting part between the auxiliary wing 3 and the flight oar 5.
Through above-mentioned technical scheme, with 2 one end rigid couplings of main wing on the lateral wall of cabin 1, the other end outwards extends along the radial direction in cabin 1 to, the quantity of main wing 2 is three and evenly lays along the circumference direction, makes whole folding unmanned aerial vehicle keep balance all the time at the flight in-process, stable flight. Meanwhile, the diameter of the main wing 2 is gradually reduced from inside to outside, so that the mechanical strength of the main wing 2 is improved; the tail end is rotatably hinged with one end of the auxiliary wing 3, the main wing 2 and the auxiliary wing 3 can be coaxially fixed through the fastening bolt, the other end of the auxiliary wing 3 is provided with a flying paddle 5, and the flying paddle 5 is a two-blade flying paddle. The design can realize that after the fastening bolt is loosened, the aileron 3 is rotated to form a complete linear wing coaxial with the main wing 2, and then the fastening bolt is screwed again to be fixed for flying; when the aircraft needs to be stored after flying, the fastening bolt is loosened again, the auxiliary wing 3 is rotated towards the cabin 1 to be attached to the wall of the cabin 1, and then the fastening bolt is screwed to fix the auxiliary wing 3 in the storage state. The flight propeller 5 is a two-blade flight propeller, and can be adjusted to be in a coaxial and linear state with the auxiliary wing 3 in a rotating mode, so that the occupied space of the flight propeller in an optional state is greatly reduced. The top of undercarriage 4 installs the bottom at cabin 1 with overturning, can make undercarriage 4 accomodate to cabin 1 bottom region or stretch out from cabin 1 bottom region through the upset, so just can further reduce whole folding unmanned aerial vehicle's size, operating space when having saved operating personnel debugging or maintaining reduces tired sense for it can keep the good operating condition of longer time.
Simultaneously, folding being close to the main wing 2 back at aileron 3, in transport or transportation, in case unmanned aerial vehicle's cabin 1 frequently takes place to rock and makes the fastening bolt unexpected not hard up, can lead to originally fixed folding state destruction and rock along with external force between aileron 3 and the main wing 2, not only expandes again and occupy great storage space, and the unexpected expansion of aileron 3 can make it receive external force to damage in addition, seriously shortens life. Therefore, a clamping arm 6 is formed on the outer wall of the nacelle 1 at a position close to the main wing 2 in a protruding manner, a clamping buckle 7 is arranged at the head of the clamping arm 6, and when the aileron 3 is folded to be close to the main wing 2, the clamping buckle 7 can be used for fixing the connecting part between the aileron 3 and the flight oar 5 in a buckling manner. So can form the binding power of dual fail-safe, effectively prevent the destruction of aileron 3 and the 2 fixed states of main wing, improve the structural stability after unmanned aerial vehicle folds greatly.
When folding unmanned aerial vehicle descends, in case the unstable folding unmanned aerial vehicle that descends loses balance or ground unevenness makes folding unmanned aerial vehicle crooked lead to main wing 2 or aileron 3 and ground contact take place the scotch or even bump and break, has shortened main wing 2 or aileron 3's life greatly, in order to avoid the emergence of above-mentioned condition, preferably, main wing 2 and/or aileron 3 are plastics and make.
In this embodiment, in order to facilitate the detachment and installation of the main wing 2 and the auxiliary wing 3 to maintain the folding unmanned aerial vehicle, it is preferable that the connection between the main wing 2 and the auxiliary wing 3 is a detachable connection.
The detachable connection mode can be any one of the quick and convenient connection modes which are common in the field, but considering the aspects of controlling the product cost and lightening the whole weight of the folding unmanned aerial vehicle, the detachable connection mode is preferably a threaded connection mode, the main wing 2 and the auxiliary wing 3 are both provided with internal thread holes, the auxiliary wing 3 can be fixed to be coaxial with the main wing 2 by sequentially penetrating the internal thread holes through bolts, or the auxiliary wing 3 can rotate around the connection part to be close to the cabin 1 by loosening the bolts.
In the practical use process of the folding unmanned aerial vehicle, when the auxiliary wing 3 and the flight oar 5 are collected, the folding unmanned aerial vehicle is easy to collide with the outer wall of the cabin 1 for scraping, and in order to prevent the cabin 1 or the auxiliary wing 3 and the flight oar 5 from being damaged after scraping for multiple times, preferably, an anti-collision strip is arranged on the outer wall of the cabin 1 in a region close to the auxiliary wing 3.
The bumper strip may be made of any flexible material commonly used in the art, but preferably, the bumper strip is a sponge strip in view of easy material availability and simple manufacturing and installation process.
When folding unmanned aerial vehicle speed is comparatively swiftly descended to the uneven landing of height, in order to avoid cabin 1 bottom or undercarriage 4 to take place violent colliding with and damage with ground, prolong undercarriage 4's life, preferably, lay the rubber pad with the region of landing surface contact on undercarriage 4.
The preferred embodiments of the present invention have been described in detail with reference to the accompanying drawings, however, the present invention is not limited to the specific details of the above embodiments, and various simple modifications can be made to the technical solution of the present invention within the technical idea of the present invention, and these simple modifications are within the protective scope of the present invention.
It should be noted that the various technical features described in the above embodiments can be combined in any suitable manner without contradiction, and the invention is not described in any way for the possible combinations in order to avoid unnecessary repetition.
In addition, any combination of the various embodiments of the present invention is also possible, and the same should be considered as the disclosure of the present invention as long as it does not depart from the spirit of the present invention.
Claims (7)
1. A folding unmanned aerial vehicle is characterized by comprising a cabin (1), a main wing (2), an auxiliary wing (3) and an undercarriage (4); wherein,
one end of each main wing (2) is fixedly connected to the outer side wall of the engine room (1), the other end of each main wing extends outwards along the radial direction of the engine room (1), and the number of the main wings (2) is three and the main wings are uniformly distributed along the circumferential direction;
the diameter of the main wing (2) is gradually reduced from inside to outside, the tail end of the main wing is rotatably hinged with one end of the auxiliary wing (3), the main wing (2) and the auxiliary wing (3) can be coaxially fixed through a fastening bolt, a flying propeller (5) is installed at the other end of the auxiliary wing (3), and the flying propeller (5) is a two-blade flying propeller;
the top end of the landing gear (4) is arranged at the bottom end of the cabin (1) in a turnover mode, and the landing gear (4) can be accommodated in the bottom area of the cabin (1) or extend out of the bottom area of the cabin (1) through turnover;
be close to on cabin (1) outer wall the outside arch of position part of main wing (2) is formed with centre gripping arm (6), centre gripping arm (6) head is provided with centre gripping and grabs knot (7), works as aileron (3) are folded to being close to when main wing (2), centre gripping is grabbed knot (7) and can be with aileron (3) with the coupling part buckle between flight oar (5) is fixed.
2. Folding drone according to claim 1, characterised in that the main wing (2) and/or the auxiliary wing (3) are made of plastic.
3. Folding drone according to claim 1, characterised in that the connection between the main wing (2) and the auxiliary wing (3) is a detachable connection.
4. A folding drone according to claim 3, characterised in that the detachable connection is a threaded connection, both the main wing (2) and the aileron (3) are provided with internal threaded holes through which bolts pass in sequence to enable the aileron (3) to be fixed coaxially to the main wing (2), or the aileron (3) can be made to rotate around the connection to approach the nacelle (1) by loosening the bolts.
5. A folding drone according to claim 1, characterised in that the outer wall of the nacelle (1) in the area close to the aileron (3) is provided with crash strips.
6. A folding drone according to claim 5, characterised in that the crash bars are sponge bars.
7. A folding drone according to claim 1, characterised in that the landing gear (4) is coated with a rubber pad in the area of contact with the landing surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810619910.6A CN108791854A (en) | 2018-06-15 | 2018-06-15 | Fold unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810619910.6A CN108791854A (en) | 2018-06-15 | 2018-06-15 | Fold unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108791854A true CN108791854A (en) | 2018-11-13 |
Family
ID=64086451
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810619910.6A Withdrawn CN108791854A (en) | 2018-06-15 | 2018-06-15 | Fold unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108791854A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113415438A (en) * | 2021-07-27 | 2021-09-21 | 南京航空航天大学 | Collapsible fuselage suitable for foreign body surveys helicopter |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205022857U (en) * | 2015-09-30 | 2016-02-10 | 湖南云顶智能科技有限公司 | Unmanned aerial vehicle horn folding mechanism and unmanned aerial vehicle |
| CN205633049U (en) * | 2016-04-08 | 2016-10-12 | 四川克瑞斯航空科技有限公司 | Collapsible many rotor unmanned aerial vehicle of horn |
| CN206068145U (en) * | 2016-08-31 | 2017-04-05 | 数字鹰科技盐城有限公司 | A kind of foldable type unmanned plane |
| CN107719660A (en) * | 2017-10-25 | 2018-02-23 | 深圳市科卫泰实业发展有限公司 | Unmanned vehicle folds horn |
| CN107878745A (en) * | 2017-12-18 | 2018-04-06 | 南京灿华光电设备有限公司 | It is a kind of to be easy to folded unmanned plane |
-
2018
- 2018-06-15 CN CN201810619910.6A patent/CN108791854A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205022857U (en) * | 2015-09-30 | 2016-02-10 | 湖南云顶智能科技有限公司 | Unmanned aerial vehicle horn folding mechanism and unmanned aerial vehicle |
| CN205633049U (en) * | 2016-04-08 | 2016-10-12 | 四川克瑞斯航空科技有限公司 | Collapsible many rotor unmanned aerial vehicle of horn |
| CN206068145U (en) * | 2016-08-31 | 2017-04-05 | 数字鹰科技盐城有限公司 | A kind of foldable type unmanned plane |
| CN107719660A (en) * | 2017-10-25 | 2018-02-23 | 深圳市科卫泰实业发展有限公司 | Unmanned vehicle folds horn |
| CN107878745A (en) * | 2017-12-18 | 2018-04-06 | 南京灿华光电设备有限公司 | It is a kind of to be easy to folded unmanned plane |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113415438A (en) * | 2021-07-27 | 2021-09-21 | 南京航空航天大学 | Collapsible fuselage suitable for foreign body surveys helicopter |
| CN113415438B (en) * | 2021-07-27 | 2022-04-08 | 南京航空航天大学 | Collapsible fuselage suitable for foreign body surveys helicopter |
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Application publication date: 20181113 |