CN108773480A - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
- Publication number
- CN108773480A CN108773480A CN201810617801.0A CN201810617801A CN108773480A CN 108773480 A CN108773480 A CN 108773480A CN 201810617801 A CN201810617801 A CN 201810617801A CN 108773480 A CN108773480 A CN 108773480A
- Authority
- CN
- China
- Prior art keywords
- wing
- cabin
- main wing
- unmanned aerial
- aerial vehicle
- 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.)
- Withdrawn
Links
- 239000004033 plastic Substances 0.000 claims description 3
- 229920003023 plastic Polymers 0.000 claims description 3
- 241001290198 Dicliptera Species 0.000 abstract 1
- 108010066057 cabin-1 Proteins 0.000 description 9
- 238000012423 maintenance Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 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
- 230000002441 reversible effect Effects 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 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
- 238000007790 scraping Methods 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
-
- 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
-
- 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
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
-
- 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
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
- B64C2025/125—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of unmanned planes, including cabin, host wing, the slave wing and undercarriage；Host wing one end is fixed on the lateral wall of cabin, and the other end extends outwardly along the radial direction of cabin, also, the quantity of host wing is for three and uniformly distributed along circumferential direction；Host wing diameter is gradually reduced from inside to outside, and end is rotationally hinged with slave wing one end, can coaxially be fixed host wing and the slave wing by fastening bolt, also, the slave wing other end is equipped with flight paddle, and flight paddle is two leaf flight paddles；The top of undercarriage is mounted on the bottom end of cabin turnablely, may make undercarriage to store to cabin bottom section or the stretching of slave cabin bottom section by overturning.The unmanned plane is simple in structure, easy to operate, can when not in use quickly fold wing and flight paddle, reduce volume, save operating space so that work is more comfortable when debugging or safeguarding.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.
Background
Along with more and more unmanned aerial vehicles, model aeroplane and model ship, the aircraft of taking photo by plane is applied to civilian field, and owing to the function and the continuous increase of lift limit journey, unmanned aerial vehicle self weight and volume also are constantly increasing to, unmanned aerial vehicle after the use is when depositing, and its wing and the 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 an unmanned aerial vehicle which is simple in structure and can save occupied space.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle which is simple in structure and convenient to operate, wings and flight propellers can be folded quickly when the unmanned aerial vehicle is not used, the size is reduced, the operation space is saved, and the unmanned aerial vehicle is more comfortable to work during debugging or maintenance.
In order to achieve the above object, the present invention provides an 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 mounted at the bottom end of the nacelle in a reversible manner, so that the landing gear can be retracted into or extended out of the bottom region of the nacelle by means of the rotation.
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 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 unmanned aerial vehicle can be further reduced, the operation space for debugging or maintenance of operators is saved, the fatigue is reduced, and the good working state of the unmanned aerial vehicle can be kept for a longer time.
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 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
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 an unmanned aerial vehicle comprising a nacelle 1, a main wing 2, an aileron 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 mounted to the bottom end of the nacelle 1 in a reversible manner, so that the landing gear 4 can be retracted into the bottom region of the nacelle 1 or extended out of the bottom region of the nacelle 1 by the rotation.
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 circumferential direction, makes whole 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 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.
When unmanned aerial vehicle descends, in case the unstable unmanned aerial vehicle of landing loses balance or ground unevenness makes the unmanned aerial vehicle crooked lead to that main wing 2 or aileron 3 and ground contact take place the scotch or even bump and break, has shortened the life of main wing 2 or aileron 3 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 for maintenance of the drone, it is preferable that the connection between the main wing 2 and the auxiliary wing 3 be 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 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 position to be close to the cabin 1 by loosening the bolts.
In the actual use process of the unmanned aerial vehicle, when the auxiliary wing 3 and the flight oar 5 are collected, the auxiliary wing 3 and the flight oar 5 are easy to collide and scrape with each other, and in order to prevent the damage to the nacelle 1 or the auxiliary wing 3 and the flight oar 5 after scraping for multiple times, preferably, an anti-collision strip is arranged on the outer wall of the nacelle 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 the unmanned aerial vehicle lands to the uneven landing of height fast violently, in order to avoid cabin 1 bottom or undercarriage 4 to take place violent colliding with and damaging 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. An unmanned aerial vehicle, characterized by 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 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 turnable way, 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 turning.
2. A drone according to claim 1, characterised in that the main wing (2) and/or the auxiliary wing (3) are made of plastic.
3. A drone according to claim 1, characterised in that the connection between the main wing (2) and the aileron (3) is a detachable connection.
4. An unmanned aerial vehicle according to claim 3, wherein the detachable connection is a threaded connection, the main wing (2) and the aileron (3) are both provided with internal threaded holes, and the aileron (3) can be fixed to be coaxial with the main wing (2) by passing bolts through the internal threaded holes in sequence, or the aileron (3) can be rotated around the connection to be close to the nacelle (1) by loosening the bolts.
5. Unmanned aerial vehicle according to claim 1, characterized in that the outer wall of the nacelle (1) in the area close to the aileron (3) is provided with crash bars.
6. The unmanned aerial vehicle of claim 5, wherein the bumper strip is a sponge strip.
7. Unmanned aerial vehicle according to claim 1, characterized in that a rubber pad is applied to the landing gear (4) in the area in contact with the landing surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810617801.0A CN108773480A (en) | 2018-06-15 | 2018-06-15 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810617801.0A CN108773480A (en) | 2018-06-15 | 2018-06-15 | Unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108773480A true CN108773480A (en) | 2018-11-09 |
Family
ID=64025148
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810617801.0A Withdrawn CN108773480A (en) | 2018-06-15 | 2018-06-15 | Unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108773480A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114212246A (en) * | 2022-01-19 | 2022-03-22 | 谢振华 | Unmanned aerial vehicle is with unpowered adaptive undercarriage |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN207433784U (en) * | 2017-11-12 | 2018-06-01 | 邓继旺 | A kind of collapsible unmanned plane horn locking mechanism |
-
2018
- 2018-06-15 CN CN201810617801.0A patent/CN108773480A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN207433784U (en) * | 2017-11-12 | 2018-06-01 | 邓继旺 | A kind of collapsible unmanned plane horn locking mechanism |
| 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 |
|---|---|---|---|---|
| CN114212246A (en) * | 2022-01-19 | 2022-03-22 | 谢振华 | Unmanned aerial vehicle is with unpowered adaptive undercarriage |
| CN114212246B (en) * | 2022-01-19 | 2023-12-22 | 国网甘肃省电力公司张掖供电公司 | Unpowered self-adaptive landing gear for unmanned aerial vehicle |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20181109 |
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| WW01 | Invention patent application withdrawn after publication |