CN106927032A - A kind of combined type quadrotor - Google Patents
A kind of combined type quadrotor Download PDFInfo
- Publication number
- CN106927032A CN106927032A CN201710194714.4A CN201710194714A CN106927032A CN 106927032 A CN106927032 A CN 106927032A CN 201710194714 A CN201710194714 A CN 201710194714A CN 106927032 A CN106927032 A CN 106927032A
- Authority
- CN
- China
- Prior art keywords
- horn
- fuselage
- undercarriage
- casing
- motor
- 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
Links
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000002787 reinforcement Effects 0.000 claims description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 2
- 229910052802 copper Inorganic materials 0.000 claims description 2
- 239000010949 copper Substances 0.000 claims description 2
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims description 2
- 239000006185 dispersion Substances 0.000 abstract description 3
- 241001391944 Commicarpus scandens Species 0.000 abstract description 2
- 230000003139 buffering effect Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 abstract description 2
- 238000009434 installation Methods 0.000 abstract description 2
- 238000003032 molecular docking Methods 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 abstract 1
- 230000035882 stress Effects 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 2
- 241001124569 Lycaenidae Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 235000014987 copper Nutrition 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009429 distress Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
-
- 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)
- Non-Portable Lighting Devices Or Systems Thereof (AREA)
- Toys (AREA)
Abstract
A kind of combined type quadrotor proposed by the present invention, including casing, fuselage, horn and undercarriage, casing, fuselage is using spliced up and down, combination is simple, intraware is easy for installation, horn is connected with fuselage using docking screwing type, junction stress is disperseed, it is not easy to break, and convenient disassembly, undercarriage upper end is vertical, middle part is angularly disposed, lower end level, and elastic patch is set, improve undercarriage toughness, improve buffering effect of the rotor craft when landing, improve landing security, in sum, rotor craft of the invention has convenient disassembly, maintenance is convenient, stress dispersion effect is good, the characteristics of landing safe, and it is easy to vanning, transport, Surface-mount LED lamp can effectively improve resolution of the rotor craft when being obstructed at night or realization, improve rotary-wing flight security.
Description
Technical field
The present invention relates to a kind of aircraft, particularly a kind of combined type quadrotor.
Background technology
Rotor craft has one or more rotors, being capable of VTOL and hovering, it is adaptable in small space or multiple
Flown in miscellaneous near-earth environment.Reconnaissance mission for small space is, it is necessary to aircraft has VTOL ability, steadily hovering energy
Power and flexible mobility.
Now the internal build of the most rotor craft that in the market is sold is generally global formation, because design is former
Cause, internals itself the stress dispersion of global formation is not uniform enough, causes, and when flight is carried out, body mechanism easily produces
Fragmentation, and then cause body to collapse, and, integral forming technique is complicated, and mould production is difficult, and yield is limited, and after damage, purchases
It is difficult.
A small number of rotor crafts uses and modeling is split between combined type theory, rotor craft each group, but still suffers from
Problem, 1, the intensity of horn it is relatively low, easily in flight course or in landing mission, there is fracture distress, and then cause flight
Device falls or damages；2nd, horn and fuselage be connected by force fix, be not only not easy to dismounting handling, junction stress compared with
Greatly, it is easily broken off；3rd, undercarriage rigidity is superfluous, and toughness is not enough, landing rapid wear.
The content of the invention
Regarding to the issue above, the present invention proposes a kind of combined type quadrotor.
To solve above technical problem, the technical scheme that the present invention is provided is:
A kind of combined type quadrotor, including casing, fuselage, horn and undercarriage, it is characterised in that the casing is by upper
Casing and lower casing are spliced, and are fastened by bolts；Casing integrally rounded rectangle, inner hollow, its fillet for being in
Horn hole is provided with four angles of rectangle, the horn hole is in annular, by 2 arches being located at respectively on upper casing and lower casing
Shape notch is constituted, and the fuselage is fixedly installed in casing, and fuselage is spliced by upper fuselage and lower fuselage, and tight by bolt
Gu；The upper fuselage and lower fuselage are provided with symmetrical battery locating piece and symmetrical horn connecting stud, the base plate of lower fuselage
Multigroup reinforcement is provided with, the lower surface of the base plate of lower fuselage is provided with mainboard fixed bolt and undercarriage contiguous block；
The horn connecting stud is provided with horn base, and described horn base one end passes through bolt and horn connecting stud phase
Even, and then it is fixedly connected with fuselage, the outer wall of horn base is provided with external screw thread, and the horn includes that connection end, horn extend
Post and motor fixing end, the connection end, horn extending column and motor fixing end are integral type structure；Horn extending column is in cylinder
Shape, is provided with through hole in horn extending column, the through hole along horn extending column be in it is cylindrical axially arranged, the motor is consolidated
The rounded annular in fixed end, the lower end of motor fixing end is provided with motor base, and the motor base is solid by bolt and motor
Screw on the lower surface of fixed end, it is affixed with motor fixing end, motor, the power transmission shaft of the motor are fixed with motor base
Stretched out from the middle part of motor fixing end institute angle annular, and be connected with propeller；The connection end is in cylinder, connection end
Horn rotary sleeve is cased with, the horn rotary sleeve is in hollow cylindrical, and its inwall is provided with internal thread, connection end insertion horn bottom
In seat, and coordinate with horn base gap, horn rotary sleeve is connected with horn whorl of base, and then realizes the company of horn and fuselage
Connect；
The quantity of the undercarriage is 4,4 undercarriages it is symmetrical it is even be distributed, undercarriage includes the vertical section of upper end, lower end
Horizontal segment and oblique section of centre, the vertical section is vertically arranged, and its upper end is provided with latch, the latch and undercarriage contiguous block
The bayonet socket corresponding matching of lower end, and then realize the connection of undercarriage and fuselage, described oblique section in angularly disposed, itself and vertical side
To in angle be α, the α is 41 °；The horizontal segment is horizontally disposed with；
Further, the side of the fuselage is provided with the controller fixed panel for fixed power source controller；
Further, the lower casing is provided with multiple holes passed through for undercarriage；
Further, one end of the horn rotary sleeve is lined with 2 coppers in the degree of lip-rounding is collected between horn rotary sleeve and connection end
Auxiliary semi-ring；
Further, the side hollow out of the undercarriage, and post the elastic patch for improving undercarriage toughness；
Further, Surface-mount LED lamp is posted in the lower end of the motor base, and the Surface-mount LED lamp is externally provided with lampshade.
Beneficial effects of the present invention are：
A kind of combined type quadrotor proposed by the present invention, including casing, fuselage, horn and undercarriage, casing, fuselage are equal
Using spliced up and down, combine simple, intraware is easy for installation, horn is connected with fuselage using docking screwing type, junction
Stress is disperseed, not easy to break, and convenient disassembly, and undercarriage upper end is vertical, middle part is angularly disposed, lower end level, and sets
Elastic patch, improves undercarriage toughness, improves buffering effect of the rotor craft when landing, and improves landing security, comprehensive
Upper described, rotor craft of the invention has convenient disassembly, overhauls the characteristics of convenient, stress dispersion effect is good, landing is safe,
And be easy to case, transport, Surface-mount LED lamp can effectively improve resolution of the rotor craft when being obstructed at night or realization, improve
Rotary-wing flight security.
Brief description of the drawings
Fig. 1 top views of the present invention.
Fuselage upward view on Fig. 2.
Fuselage upward view under Fig. 3.
Fig. 4 Section A-A figures.
Fig. 5 undercarriage sectional views.
Fig. 6 horn schematic diagrames.
Fig. 7 section B-B figures.
Specific embodiment
A kind of combined type quadrotor as depicted, including casing 1, fuselage 2, horn 3 and undercarriage 4, it is special
Levy and be, the casing 1 is spliced by upper casing 5 and lower casing 6, and is fastened by bolts；The overall rounded square of casing 1
Shape, inner hollow is provided with horn hole 7 at four angles of its round rectangle for being in, the horn hole 7 is in annular, by respectively
2 arch notches on upper casing 5 and lower casing 6 are constituted, and the fuselage 2 is fixedly installed in casing 1, and fuselage 2 is by upper
Fuselage 27 and lower fuselage 28 are spliced, and are fastened by bolts；The upper fuselage 27 and lower fuselage 28 are provided with symmetrical electricity
Pond locating piece 8 and symmetrical horn connecting stud 9, the base plate of lower fuselage 28 are provided with multigroup reinforcement 10, the bottom of lower fuselage 28
The lower surface of plate is provided with mainboard fixed bolt 11 and undercarriage contiguous block 12；
The horn connecting stud 9 is provided with horn base 13, and described one end of horn base 13 is connected spiral shell by bolt with horn
Post 9 is connected, and then is fixedly connected with fuselage 2, and the outer wall of horn base 13 is provided with external screw thread, and the horn 3 includes connection end
14th, horn extending column 15 and motor fixing end 16, the connection end 14, horn extending column 15 and motor fixing end 16 are integral type
Structure；Horn extending column 15 is provided with through hole 17 in cylinder in horn extending column 15, and the through hole 17 is along the institute of horn extending column 15
Cylindrical axially arranged, the rounded annular of the motor fixing end 16 for being in, the lower end of motor fixing end 16 is provided with motor
Base 18, the screw on lower surface that the motor base 18 passes through bolt and motor fixing end 16, with motor fixing end 16
It is affixed, it is fixed with motor 30 on motor base 18, the power transmission shaft of the motor 30 is from 16 angle annulus of motor fixing end
Stretched out in the middle part of shape, and be connected with propeller 27；The connection end 14 is cased with horn rotary sleeve 19 in cylinder, connection end 14,
The horn rotary sleeve 19 is in hollow cylindrical, and its inwall is provided with internal thread, and connection end 14 is inserted in horn base 13, and with
The gap of horn base 13 coordinates, and horn rotary sleeve 19 is threadedly coupled with horn base 13, and then realizes the company of horn 3 and fuselage 2
Connect；
The quantity of the undercarriage 4 is 4,4 undercarriages 4 it is symmetrical it is even be distributed, undercarriage 4 include upper end vertical section 20,
The horizontal segment 21 of lower end and oblique section 22 of centre, the vertical section 20 is vertically arranged, and its upper end is provided with latch 23, the latch
23 with the bayonet socket corresponding matching of the lower end of undercarriage contiguous block 12, and then realize the connection of undercarriage 4 and fuselage 2, described oblique section
22 is in angularly disposed, and it is α in angle with vertical direction institute, and the α is 41 °；The horizontal segment 21 is horizontally disposed with；
Further, the side of the fuselage 2 is provided with the controller fixed panel 24 for fixed power source controller；
Further, the lower casing 6 is provided with multiple holes passed through for undercarriage 4；
Further, one end of the horn rotary sleeve 19 is lined with 2 in the degree of lip-rounding is collected between horn rotary sleeve 19 and connection end 14
Individual auxiliary semi-ring 25 made of copper；
Further, the side hollow out of the undercarriage 4, and post the elastic patch 26 for improving the toughness of undercarriage 4；
Further, Surface-mount LED lamp 31 is posted in the lower end of the motor base 18, and the Surface-mount LED lamp 31 is externally provided with lampshade 29.
The above, the only present invention preferably specific embodiment, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
Should all cover within the scope of the present invention.Therefore, protection scope of the present invention should be with the protection domain of claims
It is defined.
Claims (6)
1. a kind of combined type quadrotor, including casing, fuselage, horn and undercarriage, it is characterised in that the casing by
Upper casing and lower casing are spliced, and are fastened by bolts；Casing integrally rounded rectangle, inner hollow, its circle for being in
Horn hole is provided with four angles of angular moment shape, the horn hole is in annular, by 2 be located at respectively on upper casing and lower casing
Arch notch is constituted, and the fuselage is fixedly installed in casing, and fuselage is spliced by upper fuselage and lower fuselage, and by bolt
Fastening；The upper fuselage and lower fuselage are provided with symmetrical battery locating piece and symmetrical horn connecting stud, the bottom of lower fuselage
Plate is provided with multigroup reinforcement, and the lower surface of the base plate of lower fuselage is provided with mainboard fixed bolt and undercarriage contiguous block；
The horn connecting stud is provided with horn base, and described horn base one end passes through bolt and horn connecting stud phase
Even, and then it is fixedly connected with fuselage, the outer wall of horn base is provided with external screw thread, and the horn includes that connection end, horn extend
Post and motor fixing end, the connection end, horn extending column and motor fixing end are integral type structure；Horn extending column is in cylinder
Shape, is provided with through hole in horn extending column, the through hole along horn extending column be in it is cylindrical axially arranged, the motor is consolidated
The rounded annular in fixed end, the lower end of motor fixing end is provided with motor base, and the motor base is solid by bolt and motor
Screw on the lower surface of fixed end, it is affixed with motor fixing end, motor, the power transmission shaft of the motor are fixed with motor base
Stretched out from the middle part of motor fixing end institute angle annular, and be connected with propeller；The connection end is in cylinder, connection end
Horn rotary sleeve is cased with, the horn rotary sleeve is in hollow cylindrical, and its inwall is provided with internal thread, connection end insertion horn bottom
In seat, and coordinate with horn base gap, horn rotary sleeve is connected with horn whorl of base, and then realizes the company of horn and fuselage
Connect；
The quantity of the undercarriage is 4,4 undercarriages it is symmetrical it is even be distributed, undercarriage includes the vertical section of upper end, lower end
Horizontal segment and oblique section of centre, the vertical section is vertically arranged, and its upper end is provided with latch, the latch and undercarriage contiguous block
The bayonet socket corresponding matching of lower end, and then realize the connection of undercarriage and fuselage, described oblique section in angularly disposed, itself and vertical side
To in angle be α, the α is 41 °；The horizontal segment is horizontally disposed with.
2. a kind of combined type quadrotor as claimed in claim 1, it is characterised in that the side of the fuselage is provided with use
In the controller fixed panel of fixed power source controller.
3. a kind of combined type quadrotor as claimed in claim 1, it is characterised in that the lower casing is provided with multiple
For the hole that undercarriage passes through.
4. a kind of combined type quadrotor as claimed in claim 1, it is characterised in that one end of the horn rotary sleeve
In the degree of lip-rounding is collected, 2 auxiliary semi-rings made of copper are lined between horn rotary sleeve and connection end.
5. a kind of combined type quadrotor as claimed in claim 1, it is characterised in that engrave the side of the undercarriage
Sky, and post the elastic patch for improving undercarriage toughness.
6. a kind of combined type quadrotor as claimed in claim 1, it is characterised in that the lower end patch of the motor base
There is Surface-mount LED lamp, the Surface-mount LED lamp is externally provided with lampshade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710194714.4A CN106927032B (en) | 2017-03-29 | 2017-03-29 | Combined four-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710194714.4A CN106927032B (en) | 2017-03-29 | 2017-03-29 | Combined four-rotor aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106927032A true CN106927032A (en) | 2017-07-07 |
| CN106927032B CN106927032B (en) | 2023-11-24 |
Family
ID=59424853
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710194714.4A Active CN106927032B (en) | 2017-03-29 | 2017-03-29 | Combined four-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106927032B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113353270A (en) * | 2021-08-11 | 2021-09-07 | 西安羚控电子科技有限公司 | Power system and flight device with same |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105035313A (en) * | 2015-06-30 | 2015-11-11 | 北京航空航天大学 | Rotated quadrotor |
| WO2016066009A1 (en) * | 2014-10-27 | 2016-05-06 | 广州极飞电子科技有限公司 | Rotorcraft, motor heat dissipation structure, connecting structure for craft arm and fuselage, and landing gear assembly/disassembly structure |
| WO2016148303A1 (en) * | 2015-03-19 | 2016-09-22 | 株式会社プロドローン | Unmanned rotorcraft, and surrounding object ranging method thereof |
| CN105984583A (en) * | 2015-02-13 | 2016-10-05 | 鸿富锦精密工业（深圳）有限公司 | Aircraft |
| WO2016192606A1 (en) * | 2015-06-04 | 2016-12-08 | 珠海星宇航空技术有限公司 | Through-beam type rotor flight arm and flight vehicle using same |
| CN106218881A (en) * | 2016-08-30 | 2016-12-14 | 辽宁壮龙无人机科技有限公司 | Vertical layout fuel power four rotor flying platform |
| CN106218884A (en) * | 2016-09-28 | 2016-12-14 | 安徽工程大学机电学院 | The portable multi-rotor aerocraft of Spliced type |
-
2017
- 2017-03-29 CN CN201710194714.4A patent/CN106927032B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016066009A1 (en) * | 2014-10-27 | 2016-05-06 | 广州极飞电子科技有限公司 | Rotorcraft, motor heat dissipation structure, connecting structure for craft arm and fuselage, and landing gear assembly/disassembly structure |
| CN105984583A (en) * | 2015-02-13 | 2016-10-05 | 鸿富锦精密工业（深圳）有限公司 | Aircraft |
| WO2016148303A1 (en) * | 2015-03-19 | 2016-09-22 | 株式会社プロドローン | Unmanned rotorcraft, and surrounding object ranging method thereof |
| WO2016192606A1 (en) * | 2015-06-04 | 2016-12-08 | 珠海星宇航空技术有限公司 | Through-beam type rotor flight arm and flight vehicle using same |
| CN105035313A (en) * | 2015-06-30 | 2015-11-11 | 北京航空航天大学 | Rotated quadrotor |
| CN106218881A (en) * | 2016-08-30 | 2016-12-14 | 辽宁壮龙无人机科技有限公司 | Vertical layout fuel power four rotor flying platform |
| CN106218884A (en) * | 2016-09-28 | 2016-12-14 | 安徽工程大学机电学院 | The portable multi-rotor aerocraft of Spliced type |
Non-Patent Citations (1)
| Title |
|---|
| 刘晓琳;韩婷: "新型可倾转旋翼的四旋翼飞行器结构设计", 计算机仿真, vol. 33, no. 3 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113353270A (en) * | 2021-08-11 | 2021-09-07 | 西安羚控电子科技有限公司 | Power system and flight device with same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106927032B (en) | 2023-11-24 |
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Effective date of registration: 20231025 Address after: 235000 No. 19, Wu Tong Road, Longhu Industrial Park, Huaibei Economic Development Zone, Anhui Applicant after: Huaibei Fengfeng Industrial Design Co.,Ltd. Address before: Building 1, No. 33 Yangzhongjiang Road, Dagang, New District, Zhenjiang City, Jiangsu Province, 212000 Applicant before: ZHENJIANG SHUNYU AIRCRAFT Co.,Ltd. |
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