CN106927032B - Combined four-rotor aircraft - Google Patents
Combined four-rotor aircraft Download PDFInfo
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- CN106927032B CN106927032B CN201710194714.4A CN201710194714A CN106927032B CN 106927032 B CN106927032 B CN 106927032B CN 201710194714 A CN201710194714 A CN 201710194714A CN 106927032 B CN106927032 B CN 106927032B
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- arm
- machine body
- machine
- landing gear
- organic
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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
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- 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
The combined type four-rotor aircraft comprises a shell, a fuselage, a horn and an undercarriage, wherein the shell and the fuselage are spliced up and down, the combination is simple, the installation of internal components is convenient, the horn and the fuselage are connected in a butt joint screwing mode, stress at the joint is dispersed and is not easy to break, the disassembly and the assembly are convenient, the upper end of the undercarriage is vertical, the middle part of the undercarriage is obliquely arranged, the lower end of the undercarriage is horizontal, and an elastic patch is arranged, so that the toughness of the undercarriage is improved, the buffering effect of the rotorcraft during landing is improved, and the landing safety is improved.
Description
Technical Field
The invention relates to an aircraft, in particular to a combined type four-rotor aircraft.
Background
The rotary wing aircraft is provided with one or more rotary wings, can vertically take off and land and hover, and is suitable for flying in a narrow space or a complex near-ground environment. For reconnaissance missions in small spaces, aircraft are required to have vertical take-off and landing capabilities, stable hover capabilities, and flexible maneuverability.
Most of the internal constructions of rotorcraft sold in the market at present are integrally formed, and due to design reasons, stress dispersion of the integrally formed internal components is not uniform enough, so that when flying, the engine body mechanism is easy to crack, and then the engine body collapses.
A few rotorcraft adopts a combined concept, and the rotorcraft is split and modeled among groups, but the problems still exist, 1, the strength of the horn is low, and the helicopter is easy to break and damage in the flight process or landing process, so that the helicopter is dropped or damaged; 2. the connection between the arm and the machine body adopts forced fixation, so that the disassembly, the assembly and the disassembly are not convenient, the stress at the connection part is large, and the fracture is easy; 3. the landing gear is excessive in rigidity, insufficient in toughness and easy to land.
Disclosure of Invention
In order to solve the problems, the invention provides a combined type quadrotor aircraft.
In order to solve the technical problems, the technical scheme provided by the invention is as follows:
the combined type four-rotor aircraft comprises a shell, a fuselage, a horn and a landing gear, and is characterized in that the shell is formed by splicing an upper shell and a lower shell and is fastened through bolts; the whole casing is round-corner rectangle, the inside is hollow, the four corners of the round-corner rectangle are provided with arm holes, the arm holes are circular ring-shaped and are formed by 2 arch-shaped notches respectively positioned on the upper casing and the lower casing, the machine body is fixedly arranged in the casing, and the machine body is formed by splicing the upper machine body and the lower machine body and is fastened by bolts; the upper machine body and the lower machine body are provided with symmetrical battery positioning blocks and symmetrical arm connecting studs, a plurality of groups of reinforcing ribs are arranged on a bottom plate of the lower machine body, and a main board fixing stud and a landing gear connecting block are arranged on the lower end face of the bottom plate of the lower machine body;
the machine arm connecting stud is provided with a machine arm base, one end of the machine arm base is connected with the machine arm connecting stud through a bolt and then fixedly connected with the machine body, the outer wall of the machine arm base is provided with external threads, the machine arm comprises a connecting end, a machine arm extending column and a motor fixing end, and the connecting end, the machine arm extending column and the motor fixing end are of an integrated structure; the motor base is fixedly connected with the motor fixing end through bolts and screw holes on the lower end face of the motor fixing end, a motor is fixedly arranged on the motor base, and a transmission shaft of the motor extends out of the middle of the angular ring shape formed by the motor fixing end and is connected with a propeller; the connecting end is cylindrical, the connecting end is sleeved with an organic arm rotating sleeve, the organic arm rotating sleeve is hollow and cylindrical, an inner thread is arranged on the inner wall of the organic arm rotating sleeve, the connecting end is inserted into the organic arm base and is in clearance fit with the organic arm base, and the organic arm rotating sleeve is in threaded connection with the organic arm base, so that the connection between the organic arm and the machine body is realized;
the number of the landing gears is 4, the 4 landing gears are symmetrically and evenly distributed, each landing gear comprises a vertical section at the upper end, a horizontal section at the lower end and an oblique section in the middle, the vertical section is vertically arranged, a latch is arranged at the upper end of each vertical section, the latch is correspondingly matched with a bayonet at the lower end of a landing gear connecting block, the landing gears are connected with a machine body, the oblique sections are obliquely arranged, an included angle formed between each oblique section and the vertical direction is alpha, and the alpha is 41 degrees; the horizontal section is horizontally arranged;
further, a controller fixing panel for fixing the power supply controller is arranged on one side of the machine body;
further, the lower shell is provided with a plurality of holes for the landing gear to pass through;
furthermore, one end of the horn rotating sleeve is in a convergent shape, and 2 auxiliary semi-rings made of copper are padded between the horn rotating sleeve and the connecting end;
furthermore, one side of the landing gear is hollowed out, and an elastic patch for improving the toughness of the landing gear is attached;
further, the lower end of the motor base is stuck with an LED patch lamp, and a lampshade is arranged outside the LED patch lamp.
The beneficial effects of the invention are as follows:
the combined type four-rotor aircraft comprises a shell, a fuselage, a horn and an undercarriage, wherein the shell and the fuselage are spliced up and down, the combination is simple, the installation of internal components is convenient, the horn and the fuselage are connected in a butt joint screwing mode, stress at the joint is dispersed and is not easy to break, the disassembly and the assembly are convenient, the upper end of the undercarriage is vertical, the middle part of the undercarriage is obliquely arranged, the lower end of the undercarriage is horizontal, and an elastic patch is arranged, so that the toughness of the undercarriage is improved, the buffering effect of the rotorcraft during landing is improved, and the landing safety is improved.
Drawings
Figure 1 is a top view of the present invention.
Fig. 2 is a bottom view of the upper body.
Figure 3 is a bottom view of the lower fuselage.
Figure 4-A-A cross-sectional view.
Figure 5 is a cross-sectional view of the landing gear.
FIG. 6 is a schematic diagram of a horn.
Fig. 7-B-B cross-sectional view.
Detailed Description
The combined type quadrotor aircraft comprises a shell 1, a fuselage 2, a horn 3 and a landing gear 4, and is characterized in that the shell 1 is formed by splicing an upper shell 5 and a lower shell 6 and is fastened through bolts; the whole casing 1 is in a round rectangle, the inside of the casing is hollow, the four corners of the round rectangle are provided with arm holes 7, the arm holes 7 are circular ring-shaped and are formed by 2 arch-shaped notches respectively positioned on the upper casing 5 and the lower casing 6, the machine body 2 is fixedly arranged in the casing 1, and the machine body 2 is formed by splicing an upper machine body 27 and a lower machine body 28 and is fastened through bolts; the upper machine body 27 and the lower machine body 28 are provided with symmetrical battery positioning blocks 8 and symmetrical arm connecting studs 9, the bottom plate of the lower machine body 28 is provided with a plurality of groups of reinforcing ribs 10, and the lower end surface of the bottom plate of the lower machine body 28 is provided with a main board fixing stud 11 and a landing gear connecting block 12;
the horn connecting stud 9 is provided with a horn base 13, one end of the horn base 13 is connected with the horn connecting stud 9 through a bolt and is further fixedly connected with the machine body 2, the outer wall of the horn base 13 is provided with external threads, the horn 3 comprises a connecting end 14, a horn extending column 15 and a motor fixing end 16, and the connecting end 14, the horn extending column 15 and the motor fixing end 16 are of an integrated structure; the horn extension column 15 is cylindrical, a through hole 17 is formed in the horn extension column 15, the through hole 17 is arranged along the cylindrical axial direction of the horn extension column 15, the motor fixing end 16 is round-angle circular, the lower end of the motor fixing end 16 is provided with a motor base 18, the motor base 18 is fixedly connected with the motor fixing end 16 through bolts and screw holes on the lower end face of the motor fixing end 16, a motor 30 is fixedly arranged on the motor base 18, and a transmission shaft of the motor 30 extends out from the middle of the round-angle circular formed by the motor fixing end 16 and is connected with a propeller 27; the connecting end 14 is cylindrical, the connecting end 14 is sleeved with an organic arm rotating sleeve 19, the organic arm rotating sleeve 19 is hollow and cylindrical, an inner thread is arranged on the inner wall of the organic arm rotating sleeve 19, the connecting end 14 is inserted into the organic arm base 13 and is in clearance fit with the organic arm base 13, and the organic arm rotating sleeve 19 is in threaded connection with the organic arm base 13, so that the connection between the organic arm 3 and the machine body 2 is realized;
the number of the landing gears 4 is 4, the 4 landing gears 4 are symmetrically and evenly distributed, the landing gear 4 comprises a vertical section 20 at the upper end, a horizontal section 21 at the lower end and an inclined section 22 in the middle, the vertical section 20 is vertically arranged, a latch 23 is arranged at the upper end of the vertical section, the latch 23 is correspondingly matched with a bayonet at the lower end of a landing gear connecting block 12, the landing gear 4 is further connected with a machine body 2, the inclined section 22 is obliquely arranged, an included angle formed between the inclined section 22 and the vertical direction is alpha, and the alpha is 41 degrees; the horizontal section 21 is horizontally arranged;
further, a controller fixing panel 24 for fixing a power supply controller is arranged on one side of the machine body 2;
further, the lower casing 6 is provided with a plurality of holes for the landing gear 4 to pass through;
furthermore, one end of the arm rotating sleeve 19 is in a convergent shape, and 2 auxiliary semi-rings 25 made of copper are padded between the arm rotating sleeve 19 and the connecting end 14;
furthermore, one side of the landing gear 4 is hollowed out, and an elastic patch 26 for improving the toughness of the landing gear 4 is attached;
further, an LED patch lamp 31 is attached to the lower end of the motor base 18, and a lampshade 29 is arranged outside the LED patch lamp 31.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.
Claims (4)
1. The combined type four-rotor aircraft comprises a shell, a fuselage, a horn and a landing gear, and is characterized in that the shell is formed by splicing an upper shell and a lower shell and is fastened through bolts; the whole casing is round-corner rectangle, the inside is hollow, the four corners of the round-corner rectangle are provided with arm holes, the arm holes are circular ring-shaped and are formed by 2 arch-shaped notches respectively positioned on the upper casing and the lower casing, the machine body is fixedly arranged in the casing, and the machine body is formed by splicing the upper machine body and the lower machine body and is fastened by bolts; the upper machine body and the lower machine body are provided with symmetrical battery positioning blocks and symmetrical arm connecting studs, a plurality of groups of reinforcing ribs are arranged on a bottom plate of the lower machine body, and a main board fixing stud and a landing gear connecting block are arranged on the lower end face of the bottom plate of the lower machine body;
the machine arm connecting stud is provided with a machine arm base, one end of the machine arm base is connected with the machine arm connecting stud through a bolt and then fixedly connected with the machine body, the outer wall of the machine arm base is provided with external threads, the machine arm comprises a connecting end, a machine arm extending column and a motor fixing end, and the connecting end, the machine arm extending column and the motor fixing end are of an integrated structure; the motor base is fixedly connected with the motor fixing end through bolts and screw holes on the lower end face of the motor fixing end, a motor is fixedly arranged on the motor base, and a transmission shaft of the motor extends out of the middle of the angular ring shape formed by the motor fixing end and is connected with a propeller; the connecting end is cylindrical, the connecting end is sleeved with an organic arm rotating sleeve, the organic arm rotating sleeve is hollow and cylindrical, an inner thread is arranged on the inner wall of the organic arm rotating sleeve, the connecting end is inserted into the organic arm base and is in clearance fit with the organic arm base, and the organic arm rotating sleeve is in threaded connection with the organic arm base, so that the connection between the organic arm and the machine body is realized;
the number of the landing gears is 4, the 4 landing gears are symmetrically and evenly distributed, each landing gear comprises a vertical section at the upper end, a horizontal section at the lower end and an oblique section in the middle, the vertical section is vertically arranged, a latch is arranged at the upper end of each vertical section, the latch is correspondingly matched with a bayonet at the lower end of a landing gear connecting block, the landing gears are connected with a machine body, the oblique sections are obliquely arranged, an included angle formed between each oblique section and the vertical direction is alpha, and the alpha is 41 degrees; the horizontal section is horizontally arranged;
one side of the machine body is provided with a controller fixing panel for fixing a power supply controller, and the lower machine shell is provided with a plurality of holes for the landing gear to pass through.
2. The combined type quadrotor aircraft of claim 1, wherein one end of the horn rotating sleeve is in a convergent shape, and 2 auxiliary semi-rings made of copper are arranged between the horn rotating sleeve and the connecting end.
3. A combined quadrotor aircraft as claimed in claim 1, wherein one side of the landing gear is hollowed out and is attached with an elastic patch for improving the toughness of the landing gear.
4. The combination type quadrotor aircraft of claim 1, wherein the lower end of the motor base is attached with an LED patch lamp, and a lamp shade is arranged outside the LED patch lamp.
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 CN106927032A (en) | 2017-07-07 |
| CN106927032B true 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) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113353270B (en) * | 2021-08-11 | 2021-12-10 | 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 |
|---|
| 新型可倾转旋翼的四旋翼飞行器结构设计;刘晓琳;韩婷;计算机仿真;33(3);全文 * |
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| Publication number | Publication date |
|---|---|
| CN106927032A (en) | 2017-07-07 |
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| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
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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| GR01 | Patent grant |