CN114180052B - A multi-rotor drone device with high wind resistance for inspection - Google Patents
A multi-rotor drone device with high wind resistance for inspection Download PDFInfo
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- CN114180052B CN114180052B CN202111508168.XA CN202111508168A CN114180052B CN 114180052 B CN114180052 B CN 114180052B CN 202111508168 A CN202111508168 A CN 202111508168A CN 114180052 B CN114180052 B CN 114180052B
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- 238000007689 inspection Methods 0.000 title claims abstract description 18
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 230000001681 protective effect Effects 0.000 claims description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction 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
- B64C27/52—Tilting of rotor bodily relative to fuselage
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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
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
-
- 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
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- 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
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
- Wind Motors (AREA)
Abstract
本发明涉及一种高抗风性巡检用多旋翼无人机装置，无人机中心板的下端面四角均固定安装有固定块，固定块上安装有机臂固定套筒，机臂固定套筒端部套装有机臂，机臂端部连接反角变形机构，反角变形机构端部连接有电机座，电机座下端安装有无刷电机，无刷电机上连接有螺旋桨；四个固定块的下端面共同连接有脚架安装板，脚架安装板的下端对称安装有脚架固定座，脚架固定座上连接有T型脚架，脚架安装板底端中心位置处安装有云台负载。本发明设计科学合理，飞行稳定，且无人机在大风情况下可以有20°上、下反角的倾斜，可承受12m/s的强风，相对于传统的无人机抗风性能增强；同时，由于电机获得了一定的倾斜角度，风道产生的平面更加光，飞行稳定性更强。
The present invention relates to a multi-rotor UAV device for inspection with high wind resistance, wherein the four corners of the lower end surface of the center plate of the UAV are fixedly installed with fixed blocks, the fixed blocks are installed with an arm fixing sleeve, the end of the arm fixing sleeve is fitted with an arm, the end of the arm is connected to a reverse angle deformation mechanism, the end of the reverse angle deformation mechanism is connected to a motor seat, the lower end of the motor seat is installed with a brushless motor, and the brushless motor is connected with a propeller; the lower end surfaces of the four fixed blocks are commonly connected with a tripod mounting plate, the lower end of the tripod mounting plate is symmetrically installed with a tripod fixing seat, the tripod fixing seat is connected with a T-shaped tripod, and a gimbal load is installed at the center position of the bottom end of the tripod mounting plate. The present invention is scientifically and reasonably designed, and the flight is stable, and the UAV can have a 20° upper and lower reverse angle tilt in strong wind conditions, and can withstand a strong wind of 12m/s, and the wind resistance performance is enhanced compared to traditional UAVs; at the same time, because the motor has a certain tilt angle, the plane generated by the wind duct is smoother and the flight stability is stronger.
Description
Technical Field
The invention belongs to the technical field of inspection, relates to an inspection unmanned aerial vehicle, and particularly relates to a multi-rotor unmanned aerial vehicle device for high-wind-resistance inspection.
Background
Unmanned aerial vehicles ("UAVs") are unmanned aerial vehicles that are operated by means of radio remote control devices and self-contained programmed control devices, collectively referred to as unmanned aerial vehicles. Unmanned aircraft tend to be more suitable for tasks that are too "fooled, messy, or dangerous" than manned aircraft. Therefore, the unmanned aerial vehicle is applied to various aspects of actual engineering. Unmanned aerial vehicle is used as the use of patrolling and examining often, saves personnel and gets into some dangerous environment.
At present, the existing inspection multi-rotor unmanned aerial vehicle is horizontally and fixedly installed with a plurality of horn and motors, and is in the inspection process, the unmanned aerial vehicle is inclined in the opposite direction wholly, and certain transverse thrust is generated to counteract wind power. When unmanned aerial vehicle wholly inclines, because the restriction of mount cloud platform and flight control stability can't realize the slope of wide-angle, under the strong wind condition, unmanned aerial vehicle relies on the transverse thrust that whole slope provided to be less than wind-force, therefore has the restriction in the wind-resistance.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a multi-rotor unmanned aerial vehicle device for high-wind-resistance inspection.
The invention solves the technical problems by the following technical proposal:
A multi-rotor unmanned aerial vehicle device for high wind resistance inspection is characterized by comprising an unmanned aerial vehicle central plate, wherein a battery compartment is arranged at the upper end of the unmanned aerial vehicle central plate, a GPS support is arranged on the outer side of the battery compartment, a GPS module is arranged on the GPS support, a shell is arranged on the GPS support, fixing blocks are fixedly arranged at four corners of the lower end face of the unmanned aerial vehicle central plate, a horn fixing sleeve is arranged on the fixing blocks, a horn is sleeved at the end part of the horn fixing sleeve, a dihedral angle deformation mechanism is connected with the end part of the horn fixing sleeve, a motor base is connected with the lower end of the motor base, a brushless motor is arranged at the lower end of the motor base, a propeller is connected to the brushless motor, foot rest mounting plates are connected to the lower end faces of the fixing blocks together, foot rest fixing seats are symmetrically arranged at the lower ends of the foot rest mounting plates, T-shaped foot rest fixing seats are connected with T-shaped foot rest, and a tripod head load is arranged at the central position of the foot rest mounting plates.
Moreover, the dihedral deformation mechanism comprises a first sleeve, an electric push rod and a second sleeve, wherein the electric push rod is arranged at the upper end of the first sleeve, the dihedral limiting block is arranged at the upper end of the second sleeve, the end part of the electric push rod is symmetrically provided with a first rotating lug, the first rotating lug is rotationally connected with the dihedral limiting block, the front end of the first sleeve is symmetrically provided with a second rotating lug, the rear end of the second sleeve is provided with a third rotating lug, and the second rotating lug is rotationally connected with the third rotating lug.
Moreover, both ends of the horizontal foot rest of the T-shaped foot rest are sleeved with protective sleeves.
Moreover, the housing is of streamlined design.
And the horn is made of carbon fiber material.
Moreover, the periphery of the battery compartment is hollowed.
The invention has the advantages and beneficial effects that:
1. The multi-rotor unmanned aerial vehicle device for high-wind-resistance inspection is stable in flight, the unmanned aerial vehicle can incline at an upper reverse angle and a lower reverse angle of 20 degrees under the condition of strong wind, can bear strong wind of 12m/s, and is enhanced in wind resistance compared with the traditional unmanned aerial vehicle, meanwhile, due to the fact that a motor obtains a certain inclination angle, a plane generated by an air duct is more lighted, and flight stability is stronger.
2. According to the multi-rotor unmanned aerial vehicle device for high-wind-resistance inspection, the structural design of the anti-angle deformation mechanism is reasonable, the electric push rod is pushed forward when encountering strong wind, the first rotating lug rotates relative to the anti-angle limiting block, so that the third rotating lug on the second sleeve rotates relative to the second rotating lug, the second sleeve can incline at a small angle, the propeller and the motor of the unmanned aerial vehicle incline at a small angle, and the wind resistance is improved.
3. According to the multi-rotor unmanned aerial vehicle device for high-wind-resistance inspection, the two ends of the horizontal foot rest of the T-shaped foot rest are sleeved with the protection sleeves, so that the T-shaped foot rest is protected and buffered, and friction damage is reduced when the T-shaped foot rest is contacted with other equipment or falls to the ground.
4. According to the multi-rotor unmanned aerial vehicle device for high-wind-resistance inspection, the shell is of streamline design, wind resistance is reduced, and wind resistance can be improved to a certain extent.
5. The multi-rotor unmanned aerial vehicle device for high-wind-resistance inspection is characterized in that the horn is made of carbon fiber materials, so that the weight of the horn is reduced, and the flight resistance of the unmanned aerial vehicle is reduced.
6. According to the multi-rotor unmanned aerial vehicle device for high-wind-resistance inspection, the periphery of the battery bin is hollowed, so that the weight is reduced, and meanwhile, the ventilation and heat dissipation of the battery bin are increased.
Drawings
FIG. 1 is a schematic view of the structure of the present invention (with the housing removed);
Fig. 2 is an enlarged view of a portion a of fig. 1;
FIG. 3 is a schematic diagram of the structure of the present invention;
FIG. 4 is a front view of the present invention;
fig. 5 is a left side view of the present invention.
Description of the reference numerals
The unmanned aerial vehicle comprises a 1-unmanned aerial vehicle central plate, a 2-GPS bracket, a 3-battery bin, a 4-horn fixing sleeve, a 5-horn, a 6-dihedral angle deformation mechanism, a 7-propeller, an 8-motor seat, a 9-brushless motor, a 10-fixing block, an 11-foot rest mounting plate, a 12-foot rest fixing seat, a 13-tripod head load, a 14-protection sleeve, a 15-horizontal foot rest, a 16-T-shaped foot rest, a 17-shell, a 18-electric push rod, a 19-first sleeve, a 20-second rotating lug, a 21-third rotating lug, a 22-dihedral angle limiting block, a 23-first rotating lug and a 24-second sleeve.
Detailed Description
The invention is further illustrated by the following examples, which are intended to be illustrative only and not limiting in any way.
A multi-rotor unmanned aerial vehicle device for high wind resistance inspection is characterized by comprising an unmanned aerial vehicle central plate 1, wherein a battery bin 3 is arranged at the upper end of the unmanned aerial vehicle central plate 1, a GPS support 2 is arranged on the outer side of the battery bin 3, a GPS module is arranged on the GPS support 2, a shell 17 is arranged on the GPS support 2, fixing blocks 10 are fixedly arranged at four corners of the lower end face of the unmanned aerial vehicle central plate 1, a horn fixing sleeve 4 is arranged on the fixing blocks 10, a horn 5 is sleeved at the end part of the horn fixing sleeve 4, a dihedral angle deformation mechanism 6 is connected to the end part of the horn 5, a motor base 8 is connected to the end part of the dihedral angle deformation mechanism 6, a brushless motor 9 is arranged at the lower end of the motor base 8, a propeller 7 is connected to the brushless motor 9, foot rest 11 is jointly connected to the lower end faces of the fixing blocks 10, foot rest fixing seats 12 are symmetrically arranged at the lower ends of the foot rest 11, T-shaped foot rest 16 are connected to the fixing seats 12, and a cloud rest load 13 is arranged at the central position of the bottom end of the foot rest 11.
The unmanned aerial vehicle has stable flight, can incline at an upper reverse angle and a lower reverse angle of 20 degrees under the condition of strong wind, can bear strong wind of 12m/s, and has stronger wind resistance than the traditional unmanned aerial vehicle, and meanwhile, the plane generated by the air duct is more lighted and has stronger flight stability due to a certain inclination angle obtained by the motor.
The anti-angle deformation mechanism 6 comprises a first sleeve 19, an electric push rod 18 and a second sleeve 24, wherein the electric push rod 18 is installed at the upper end of the first sleeve 19, an anti-angle limiting block 22 is installed at the upper end of the second sleeve 24, a first rotating lug 23 is symmetrically installed at the end part of the electric push rod 18, the first rotating lug 23 is rotationally connected with the anti-angle limiting block 22, a second rotating lug 20 is symmetrically arranged at the front end of the first sleeve 19, a third rotating lug 21 is arranged at the rear end of the second sleeve 24, the second rotating lug 20 is rotationally connected with the third rotating lug 21, the anti-angle deformation mechanism is reasonable in structural design, the electric push rod is pushed forward when encountering heavy wind, the first rotating lug rotates relative to the anti-angle limiting block, and therefore the third rotating lug on the second sleeve rotates relative to the second rotating lug, and the second sleeve inclines at a small angle, so that the propeller and a motor of the unmanned aerial vehicle incline at a small angle, and the wind resistance is improved.
According to the invention, when a strong wind exists, the motor facing the wind can obtain a 20-degree downward dihedral angle through the extension of the electric push rod of the dihedral angle deformation mechanism, the motor push rod of the leeward motor is contracted to enable the motor to obtain a 20-degree upward dihedral angle, so that the motor can generate transverse thrust under the condition that the unmanned aerial vehicle body is horizontal, and the main body can offset the strong wind only by small-amplitude inclination under a larger wind environment, thereby realizing the increase of wind resistance.
The two ends of the horizontal foot rest 15 of the T-shaped foot rest 16 are sleeved with the protection sleeves 14, so that the T-shaped foot rest is protected and buffered, and friction damage is reduced when the T-shaped foot rest is contacted with other equipment or falls to the ground.
The housing 17 is of streamlined design, reduces windage, and can improve wind resistance to a certain extent.
The horn 5 is made of carbon fiber material, reduces the weight of the horn, and reduces the flight resistance of the unmanned aerial vehicle.
The periphery of the battery compartment 3 is hollowed out, so that the weight is reduced, and meanwhile, the ventilation and heat dissipation of the battery compartment are increased.
The working principle of the invention is as follows:
the unmanned aerial vehicle starts the motor to drive the screw to rotate, the unmanned aerial vehicle takes off, the motor is in a horizontal state at this moment, in order to obtain the better duration;
When the unmanned aerial vehicle encounters strong wind, the motor of the unmanned aerial vehicle facing the wind can extend through the electric push rod of the dihedral angle deformation mechanism to enable the motor to obtain 20 degrees of dihedral angle, the motor of the unmanned aerial vehicle leeward can shorten through the electric push rod of the dihedral angle deformation mechanism to enable the motor to obtain 20 degrees of dihedral angle, the thrust generated by the motor can generate transverse component force to resist the transverse wind under the condition that the unmanned aerial vehicle body is horizontal, and the load such as a cradle head carried by the unmanned aerial vehicle can be more stable under the condition that the unmanned aerial vehicle body is horizontal, so that the load such as the cradle head is unstable in work due to the large-amplitude shaking of the unmanned aerial vehicle body is avoided;
When the wind power borne by the unmanned aerial vehicle is increased, the unmanned aerial vehicle motor is inclined by an angle after obtaining the dihedral angle, so that the transverse component force of the thrust of the motor is increased, better wind resistance can be obtained, and compared with the traditional unmanned aerial vehicle, the unmanned aerial vehicle has the advantages that the inclination of the unmanned aerial vehicle body is 20 degrees smaller, the better wind resistance can be obtained on the premise that the load such as a cradle head works stably, and when the wind becomes small, the motor of the unmanned aerial vehicle becomes horizontal again, so that better cruising performance can be obtained.
Although the embodiments of the present invention and the accompanying drawings have been disclosed for illustrative purposes, those skilled in the art will appreciate that various substitutions, changes and modifications are possible without departing from the spirit and scope of the invention and the appended claims, and therefore the scope of the invention is not limited to the embodiments and the disclosure of the drawings.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111508168.XA CN114180052B (en) | 2021-12-10 | 2021-12-10 | A multi-rotor drone device with high wind resistance for inspection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111508168.XA CN114180052B (en) | 2021-12-10 | 2021-12-10 | A multi-rotor drone device with high wind resistance for inspection |
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| Publication Number | Publication Date |
|---|---|
| CN114180052A CN114180052A (en) | 2022-03-15 |
| CN114180052B true CN114180052B (en) | 2025-01-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111508168.XA Active CN114180052B (en) | 2021-12-10 | 2021-12-10 | A multi-rotor drone device with high wind resistance for inspection |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116692047B (en) * | 2023-07-07 | 2026-02-17 | 中国电子科技集团公司第五十四研究所 | A streamlined sea-air cross-domain unmanned aerial vehicle |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292468A (en) * | 2015-11-06 | 2016-02-03 | 极翼机器人(上海)有限公司 | Multi-rotor-wing unmanned aircraft |
| JP2019026233A (en) * | 2017-07-27 | 2019-02-21 | 株式会社Ｍｍラボ | Unmanned aircraft |
| JP2019077207A (en) * | 2017-10-20 | 2019-05-23 | 株式会社プロドローン | Rotary wing aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109314452B (en) * | 2016-06-21 | 2021-02-19 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle with inclined propellers and related systems and methods |
| CN206569250U (en) * | 2017-03-24 | 2017-10-20 | 四川建筑职业技术学院 | A kind of umbrella folding frame at adjustable unmanned plane horn angle of inclination |
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- 2021-12-10 CN CN202111508168.XA patent/CN114180052B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292468A (en) * | 2015-11-06 | 2016-02-03 | 极翼机器人(上海)有限公司 | Multi-rotor-wing unmanned aircraft |
| JP2019026233A (en) * | 2017-07-27 | 2019-02-21 | 株式会社Ｍｍラボ | Unmanned aircraft |
| JP2019077207A (en) * | 2017-10-20 | 2019-05-23 | 株式会社プロドローン | Rotary wing aircraft |
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| CN114180052A (en) | 2022-03-15 |
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