CN107600426B - Single-power-driven variable-pitch multi-rotor unmanned aerial vehicle - Google Patents
Single-power-driven variable-pitch multi-rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN107600426B CN107600426B CN201711034034.2A CN201711034034A CN107600426B CN 107600426 B CN107600426 B CN 107600426B CN 201711034034 A CN201711034034 A CN 201711034034A CN 107600426 B CN107600426 B CN 107600426B
- Authority
- CN
- China
- Prior art keywords
- plate
- fixed
- transmission
- support plate
- unmanned aerial
- 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.)
- Active
Links
- 230000005540 biological transmission Effects 0.000 claims abstract description 78
- 238000005192 partition Methods 0.000 claims description 28
- 238000012423 maintenance Methods 0.000 abstract description 9
- 238000000034 method Methods 0.000 abstract description 5
- 230000033001 locomotion Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 5
- 239000000725 suspension Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005253 cladding Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Landscapes
- Friction Gearing (AREA)
- Toys (AREA)
Abstract
The invention relates to the technical field of unmanned aerial vehicles, in particular to a single-power-driven variable-pitch multi-rotor unmanned aerial vehicle which comprises a frame, a driving device, a rotor mechanism and a controller, wherein the frame is arranged on the frame; the frame comprises an upper supporting plate assembly, a lower supporting plate assembly and a plurality of connecting rods; support rods are fixed on two sides of the upper support plate assembly relatively, and hanging beams are fixed on the lower parts of the support rods respectively; the driving device comprises an engine, a transmission mechanism and a single power source for providing energy for the engine, wherein the output end of the engine is connected with the input end of the transmission mechanism, and the output end of the transmission mechanism is respectively connected with the transmission shaft of the torque-converting propeller through a universal transmission shaft. The invention has simple structure and novel design, can ensure the stability in the flying process, the driving device provides power through a single engine, the single power drives the variable pitch multiple rotors to move, the probability of flying faults is reduced under the condition of effectively ensuring the range and the load, the maintenance workload is small, the energy utilization rate is high, the operation is convenient, and the running is stable and reliable.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a single-power-driven variable-pitch multi-rotor unmanned aerial vehicle.
Background
In recent years, unmanned aerial vehicles develop in the market, and multi-rotor unmanned aerial vehicles rapidly acquire attention of a wide consumer group with the advantages of excellent control performance, convenience in vertical take-off and landing and the like, so that the multi-rotor unmanned aerial vehicles become the hottest product so far. Compared with other unmanned aerial vehicles, the multi-rotor unmanned aerial vehicle has the advantages of being capable of taking off and landing vertically and spiraling at fixed points; compared with a single rotor helicopter, the helicopter has the advantages of simple mechanical structure, high safety, low use cost and the like because of no tail rotor device. Therefore, the multi-rotor unmanned aerial vehicle is applied to various aspects, such as searching and rescuing, fire-fighting, video, entertainment, logistics and the like, and in recent years, the application of the unmanned aerial vehicle in the agricultural direction is also beginning to develop under the influence of agricultural automation, but the application of the multi-rotor unmanned aerial vehicle is not widely applied under the limitation of the structure and energy power of the existing multi-rotor unmanned aerial vehicle, and the load and the endurance time of the multi-rotor unmanned aerial vehicle become important factors for restricting the development of the multi-rotor unmanned aerial vehicle. At present, many rotor unmanned aerial vehicle on the market mainly can divide into two types, and oil moves and electronic, and electronic adoption is supplied power by the power, and a plurality of motors drive a plurality of screw and provide the lift, receive the influence of motor power, and its range and load receive very big restriction, and many rotor unmanned aerial vehicle that oil moved is one kind and is passed through the generator electricity generation by the engine and drive the motor, and another kind is a plurality of screw of being driven by a plurality of engines, has caused the low energy utilization, makes, uses and maintains the problem that the cost is high, and range and load have received the very big restriction of unmanned aerial vehicle volume dead weight.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the single-power-driven variable-pitch multi-rotor unmanned aerial vehicle which is simple in structure, novel and reasonable in design, energy-saving, consumption-reducing and high in energy utilization rate.
According to the design scheme provided by the invention, the single-power-driven variable-pitch multi-rotor unmanned aerial vehicle comprises a frame, a driving device, a rotor mechanism and a controller, wherein the rotor mechanism comprises a plurality of torque-converting propellers and propeller supports corresponding to the torque-converting propellers, the torque-converting propellers are fixed with the frame through the propeller supports, and the frame comprises an upper support plate assembly, a lower support plate assembly and a plurality of connecting rods for connecting and fixing the upper support plate assembly and the lower support plate assembly; support rods are fixed on two sides of the upper support plate assembly relatively, and hanging beams are fixed on the lower parts of the support rods respectively; the driving device comprises an engine, a transmission mechanism and a single power source for providing energy for the engine, wherein the output end of the engine is connected with the input end of the transmission mechanism, and the output end of the transmission mechanism is respectively connected with the transmission shaft of the torque-converting propeller through a universal transmission shaft.
Above-mentioned, lower backup pad subassembly contain relative parallel arrangement's baffle first, baffle second, baffle third and bottom plate, be provided with the clearance between the adjacent two, all be provided with the connecting rod mounting hole that is used for fixed connecting rod and the centre bore that is used for fixed mounting drive mechanism on baffle first, baffle second, baffle third and the bottom plate, the engine is fixed on baffle first.
Preferably, the transmission mechanism comprises a driving gear, a driven gear I, a driven gear II, a continuously variable transmission, a transmission gear, two forward output shafts and two reverse output shafts, wherein the transmission gear is respectively provided with one end of the forward output shaft and the other end of the reverse output shaft in the same direction as the forward output shaft, the forward output shafts and the reverse output shafts are arranged in a staggered mode, the output shaft of the transmitter is connected with the driving gear, the driving gear is respectively meshed with the transmission gear on the driven gear I and the forward output shaft, the driven gear I is connected with the input end of the continuously variable transmission, the output end of the continuously variable transmission is connected with the driven gear II, and the driven gear II is respectively meshed with the transmission gear on the reverse output shaft.
Furthermore, the driving gear and the driven gear are fixed between the first partition plate and the second partition plate, the continuously variable transmission is fixed between the second partition plate and the third partition plate, and the driven gear is fixed between the third partition plate and the bottom plate.
The universal transmission shaft comprises a transmission shaft and universal joints arranged at two ends of the transmission shaft; preferably, the single power source is an oil tank or a generator.
The upper support plate assembly comprises an upper support plate I and an upper support plate II which are arranged in parallel, and the upper support plate I and the upper support plate II are arranged at intervals; mounting holes for fixing the connecting rods are formed in the first upper supporting plate and the second upper supporting plate; the support rod fixing seat used for fixing the support rod is arranged between the first upper support plate and the second upper support plate and fixed on two opposite sides of the first support plate and the second support plate through locking pieces.
Preferably, the support rod fixing seat comprises a seat body and a first mounting hole which is arranged on the seat body and used for mounting the support rod, and the first mounting hole is arranged in a gradient manner.
Above-mentioned, screw support be the support horizontal pole, the one end of support horizontal pole is fixed with last backup pad subassembly through the fixing base, the other end passes through the supporting seat and is connected with the screw transmission shaft.
Preferably, the end part of the supporting seat is provided with an extension plate, the extension plate is provided with a mounting through hole for mounting the propeller transmission shaft, and a bearing for connecting the propeller transmission shaft is arranged in the mounting through hole.
Preferably, the fixing seat comprises a two-half fixing seat body and a cross rod mounting hole which is arranged on the two-half fixing seat body and used for mounting the supporting cross rod, and the cross rod mounting hole is arranged in a gradient manner; the support cross rod is arranged in the two-half fixing seat body through the cross rod mounting hole, and the locking piece is fixed with the upper support plate assembly.
The invention has the beneficial effects that:
The invention has simple structure, novel and reasonable design, solves the problems of limited range and load, low energy utilization rate, inconvenient maintenance and the like of the existing unmanned aerial vehicle, can realize power supply through a single engine, has small number of used engines, small maintenance workload of a power device, and low manufacturing, using and maintenance costs, and each part is symmetrically arranged along the upper and lower support plate assemblies, so that the unmanned aerial vehicle is easier to keep stable in the flying process, and has high energy utilization rate; simultaneously, the load and range of the multiple rotors are greatly improved; the rotating speed of all propellers is changed by changing the rotating speed of an engine, the vertical movement of a plurality of rotors is controlled, the rotating speed of a forward output shaft is increased or reduced by adjusting a stepless speed changer, so that the plurality of rotors do yaw movement, the lift force of the corresponding propellers is changed by changing the pitch of the variable pitch propellers, and the rolling and pitching movement of the multi-rotor aircraft is controlled, so that the operation is convenient and quick, and the running is stable and reliable; and the volume and weight of the product are effectively improved, the range and the load of the product are further increased, and the product has good market popularization value.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a side view of the present invention;
FIG. 3 is a schematic diagram of the arrangement of the forward and reverse output shafts in an embodiment;
FIG. 4 is a schematic diagram of a transmission mechanism in an embodiment;
FIG. 5 is a side view of the transmission in an embodiment;
FIG. 6 is a schematic view of a universal joint structure according to an embodiment;
FIG. 7 is a propeller shaft connection schematic diagram in an embodiment;
FIG. 8 is one of the frame structure intents in an embodiment;
Fig. 9 is a second schematic diagram of a frame structure in the embodiment.
Detailed Description
In the figure, reference numeral 1 represents a torque propeller, reference numeral 11 represents a torque propeller transmission shaft, reference numeral 2 represents an upper support plate assembly, reference numeral 21 represents an upper support plate assembly, reference numeral 22 represents an upper support plate assembly, reference numeral 3 represents a lower support plate assembly, reference numeral 3a represents a bottom plate, reference numeral 3b represents a third partition plate, reference numeral 3c represents a second partition plate, reference numeral 3d represents a first partition plate, a1, a2 represents a forward output shaft, b1, b2 represents a reverse output shaft, reference numeral 31 represents a plate body, reference numeral 32 represents a mounting hole of a forward or reverse transmission shaft, reference numeral 33 represents a connecting rod mounting hole, reference numeral 34 represents a central shaft mounting hole, reference numeral 35 represents a transmission gear one-shaft mounting hole, reference numeral 4 represents a support rod, reference numeral 41 represents a support rod fixing seat, reference numeral 42 represents a mounting hole one, reference numeral 5 represents a suspension beam, reference numeral 6 represents a support cross rod, reference numeral 61 represents a fixing seat, reference numeral 62 represents a cross rod mounting hole, reference numeral 63 represents a support seat, reference numeral 64 represents an extension plate, reference numeral 7 represents a universal transmission shaft, reference numeral 8 represents a connecting rod, reference numeral 9 represents an engine, reference numeral 10 represents a transmission mechanism, reference numeral 101 represents a driving gear, reference numeral 102 represents a driven gear, reference numeral 103 represents a driven gear one-shaft, reference numeral 103 represents a stepless gear one-shaft, reference numeral 104 represents a step-down gear one-shaft, reference numeral 105, a driven gear 105, a forward output shaft or a reverse transmission shaft 108 represents a transmission shaft.
The present invention will be described in further detail with reference to the accompanying drawings and technical schemes, and embodiments of the present invention will be described in detail by means of preferred examples, but the embodiments of the present invention are not limited thereto.
Referring to fig. 1, an embodiment of a single-power-driven variable pitch multi-rotor unmanned aerial vehicle comprises a frame, a driving device, a rotor mechanism and a controller, wherein the rotor mechanism comprises a plurality of torque-converting propellers and propeller supports corresponding to the torque-converting propellers, the torque-converting propellers are fixed with the frame through the propeller supports, and the frame comprises an upper support plate assembly, a lower support plate assembly and a plurality of connecting rods for connecting and fixing the upper support plate assembly and the lower support plate assembly; support rods are fixed on two sides of the upper support plate assembly relatively, and hanging beams are fixed on the lower parts of the support rods respectively; the driving device comprises an engine, a transmission mechanism and a single power source for providing energy for the engine, wherein the output end of the engine is connected with the input end of the transmission mechanism, and the output end of the transmission mechanism is respectively connected with the transmission shaft of the torque-converting propeller through a universal transmission shaft. Each spare part can be designed to set up for following upper and lower backup pad subassembly center perpendicular symmetry, can guarantee the stability in the flight, and drive arrangement provides power through single engine, and single power drive pitch-variable many rotor motions reduces the probability that flight trouble takes place under the circumstances of effectively guaranteeing range and load, and maintenance work load is little, and the energy utilization is high.
Preferably, referring to fig. 2, the lower support plate assembly comprises a first partition plate, a second partition plate, a third partition plate and a bottom plate which are relatively arranged in parallel, gaps are arranged between the first partition plate, the second partition plate, the third partition plate and the bottom plate, connecting rod mounting holes for fixing connecting rods and center holes for fixedly mounting a transmission mechanism are formed in the first partition plate, the second partition plate, the third partition plate and the bottom plate, and the engine is fixed on the first partition plate and is simple in structure and low in maintenance cost.
Referring to fig. 3 to 5, the transmission mechanism comprises a driving gear, a driven gear I, a driven gear II, a continuously variable transmission, a transmission gear, two forward output shafts and two reverse output shafts, wherein the transmission gear is respectively provided with one end of the forward output shaft and the other end of the reverse output shaft in the same direction as the forward output shaft, the forward output shafts and the reverse output shafts are arranged in a staggered manner, the output shaft of the transmitter is connected with the driving gear, the driving gear is respectively meshed with the driven gear I and the transmission gear on the forward output shaft, the driven gear I is connected with the input end of the continuously variable transmission, the output end of the continuously variable transmission is connected with the driven gear II, and the driven gear II is respectively meshed with the transmission gear on the reverse output shaft. The forward output shafts and the reverse output shafts are arranged in a staggered manner, so that the adjacent two output directions are opposite; the engine drives the driving gear, one part of the driving gear is used for driving the driven gear meshed with the driving gear, the other part of the driving gear is meshed with the transmission gear of the forward or reverse output shaft to output positive or reverse torque, the driven gear is connected with the input shaft of the continuously variable transmission to drive the continuously variable transmission, the output end of the continuously variable transmission is connected with the driven gear to drive the driven gear, and the driven gear is meshed with the transmission gear of the reverse or forward output shaft to output negative or forward torque. The rotating speed of all propellers is changed by changing the rotating speed of an engine, so that the vertical movement of a plurality of rotors is controlled; the rotating speed of the forward output shaft is increased or reduced by adjusting the stepless speed changer, so that the multiple rotors do yaw motion; the pitch of the variable-pitch propeller is changed, the lift force of the corresponding propeller is changed, and the rolling and pitching motions of the multi-rotor aircraft are controlled; the structure that a power device is arranged for each rotor wing is omitted, the power device is adopted to drive the propellers of the plurality of rotor wings to rotate, the power output is uniform, and the flying is more stable; meanwhile, as the propellers of the multiple rotors have the same rotating speed, the lifting force and the blade angle of each rotor can be uniformly controlled and regulated by the controller, the control is simpler and easier, the change of the rotating speed is replaced by the change of the pitch, the output power of the engine can be always maintained at a more economic rotating speed, the energy is saved, and the endurance is improved.
Furthermore, the driving gear and the driven gear are fixed between the first partition plate and the second partition plate, the continuously variable transmission is fixed between the second partition plate and the third partition plate, and the second driven gear is fixed between the third partition plate and the bottom plate; compact structure, reasonable in design effectively guarantees the stability, the reliability of drive mechanism work.
The universal transmission shaft comprises a transmission shaft and universal joints arranged at two ends of the transmission shaft, and the universal joints are shown in fig. 6 and can be formed by connecting seats comprising a pair of hinge buckles with the relative orientation of 90 degrees; according to the design demand, universal joint also adopts spherical joint structure, and the cover has the hemisphere shell on the ball that rotates in the spherical joint structure, and the ball that rotates can carry out universal rotation in hemisphere shell cladding scope, and ball and hemisphere shell are fixed with two parts that wait to be connected respectively. Because the belt has good elasticity, can alleviate impact and vibration at work, the steady noiseless of motion can prevent other parts damage, plays the safety protection effect, consequently, in the use, this universal drive shaft's structure also accessible belt drive realizes, through set up the belt pulley on positive or negative output axle and screw transmission shaft, realizes through the transmission belt, simple structure makes easily, installation and easy maintenance, and the cost is lower.
Furthermore, the single power source is an oil tank or a generator, and the oil tank or the generator provides fuel or electric energy for the engine, so that the endurance and the loading capacity of the multi-rotor unmanned aerial vehicle are greatly enhanced.
As shown in fig. 8 and 9, the upper support plate assembly includes an upper support plate one and an upper support plate two disposed parallel to each other, and disposed at a distance from each other; mounting holes for fixing the connecting rods are formed in the first upper supporting plate and the second upper supporting plate; the support rod fixing seat used for fixing the support rods is arranged between the first support plate and the second support plate, the support rod fixing seat is fixed on two opposite sides of the first support plate and the second support plate through locking pieces, and the support rods are symmetrically arranged on two sides of the first support plate and the second support plate, so that stability in the flying process is effectively guaranteed.
Preferably, the support rod fixing seat comprises a seat body and a first mounting hole which is arranged on the seat body and used for mounting the support rod, and the first mounting hole is arranged in a gradient manner; the slope setting of mounting hole can guarantee that the bracing piece presents certain angle and fixes between last backup pad subassembly and suspension beam, and suspension beam sets up perpendicularly with the bracing piece, guarantees the stability of flight.
Above-mentioned, the screw support is the support horizontal pole, and the one end of support horizontal pole is fixed with last backup pad subassembly through the fixing base, and the other end passes through the supporting seat to be connected with the screw transmission shaft, and fixed stay torque conversion screw guarantees flight stationarity, reliability.
Preferably, as shown in fig. 7, the end part of the supporting seat is provided with an extension plate, the extension plate is provided with a mounting through hole for mounting the propeller transmission shaft, a bearing for connecting the propeller transmission shaft is arranged in the mounting through hole, so that the friction coefficient of the propeller transmission shaft in the moving process is reduced, the rotation precision of the propeller transmission shaft is ensured, the flight fault in the flight process is effectively avoided, and the maintenance probability is reduced.
Preferably, the fixing seat comprises a two-half fixing seat body and a cross rod mounting hole which is arranged on the two-half fixing seat body and used for mounting the supporting cross rod, and the cross rod mounting hole is arranged in a gradient manner; the support cross rod is arranged in the two-half fixing seat body through the cross rod mounting hole, and the locking piece is fixed with the upper support plate assembly. The structure of the two-half fixing seat body is characterized in that the supporting cross rod is fixed on the upper supporting plate assembly through the locking piece, the design is reasonable, the disassembly, the assembly and the maintenance are convenient, and the using function effect is good.
The invention freely realizes hovering and free movement in space by driving the multi-torque propeller through single power, has high energy utilization rate, good flexibility and excellent control performance and convenient performance of vertical lifting; the device has the advantages of simple structure, stable mechanical property, low cost and high cost performance, and can be widely applied to various aspects such as search and rescue, fire control, film and television, entertainment, logistics, agricultural automation and the like.
The present invention is not limited to the above-described embodiments, and various changes may be made thereto by those skilled in the art, but any equivalent or similar changes to the present invention should be construed to be included within the scope of the claims of the present invention.
Claims (5)
1. The single-power-driven variable-pitch multi-rotor unmanned aerial vehicle comprises a frame, a driving device, a rotor mechanism and a controller, wherein the rotor mechanism comprises a plurality of variable-pitch propellers and propeller supports corresponding to the variable-pitch propellers, and the variable-pitch propellers are fixed with the frame through the propeller supports; support rods are fixed on two sides of the upper support plate assembly relatively, and hanging beams are fixed on the lower parts of the support rods respectively; the driving device comprises an engine, a transmission mechanism and a single power source for providing energy for the engine, wherein the output end of the engine is connected with the input end of the transmission mechanism, and the output end of the transmission mechanism is respectively connected with the transmission shaft of the torque-converting propeller through a universal transmission shaft; the lower support plate assembly comprises a first baffle plate, a second baffle plate, a third baffle plate and a bottom plate which are relatively arranged in parallel, a gap is arranged between the two adjacent baffle plates, connecting rod mounting holes for fixing connecting rods and a central hole for fixedly mounting a transmission mechanism are formed in each of the first baffle plate, the second baffle plate, the third baffle plate and the bottom plate, and the engine is fixed on the first baffle plate; the transmission mechanism comprises a driving gear, a driven gear I, a driven gear II, a continuously variable transmission, a transmission gear, two forward output shafts and two reverse output shafts, wherein the transmission gear is respectively provided with one end of the forward output shaft and the other end of the reverse output shaft in the same direction as the forward output shaft; the driving gear and the driven gear are fixed between the first partition plate and the second partition plate, the continuously variable transmission is fixed between the second partition plate and the third partition plate, and the driven gear is fixed between the third partition plate and the bottom plate; the upper support plate assembly comprises an upper support plate I and an upper support plate II which are arranged in parallel, and the upper support plate I and the upper support plate II are arranged at intervals; mounting holes for fixing the connecting rods are formed in the first upper supporting plate and the second upper supporting plate; a support rod fixing seat for fixing the support rod is arranged between the first upper support plate and the second upper support plate, and the support rod fixing seat is fixed on two opposite sides of the first support plate and the second support plate through locking pieces; the screw support be the support horizontal pole, the one end of support horizontal pole is fixed with last backup pad subassembly through the fixing base, the other end passes through the supporting seat and is connected with the screw transmission shaft.
2. The single power driven variable pitch multi-rotor unmanned aerial vehicle of claim 1, wherein the universal drive shaft comprises a drive shaft and universal joints arranged at two ends of the drive shaft; preferably, the single power source is an oil tank or a generator.
3. The single-power-driven variable-pitch multi-rotor unmanned aerial vehicle of claim 1, wherein the support rod fixing seat comprises a seat body and a first mounting hole which is arranged on the seat body and used for mounting the support rod, and the first mounting hole is arranged in a gradient manner.
4. The single-power-driven variable-pitch multi-rotor unmanned aerial vehicle according to claim 1, wherein the end part of the supporting seat is provided with an extension plate, the extension plate is provided with a mounting through hole for mounting a propeller transmission shaft, and a bearing for connecting the propeller transmission shaft is arranged in the mounting through hole.
5. The single-power-driven variable pitch multi-rotor unmanned aerial vehicle of claim 1, wherein the fixing base comprises a two-half fixing base body and a cross rod mounting hole arranged on the two-half fixing base body and used for mounting a supporting cross rod, and the cross rod mounting hole is arranged in a gradient manner; the support cross rod is arranged in the two-half fixing seat body through the cross rod mounting hole, and the locking piece is fixed with the upper support plate assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711034034.2A CN107600426B (en) | 2017-10-30 | 2017-10-30 | Single-power-driven variable-pitch multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711034034.2A CN107600426B (en) | 2017-10-30 | 2017-10-30 | Single-power-driven variable-pitch multi-rotor unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107600426A CN107600426A (en) | 2018-01-19 |
| CN107600426B true CN107600426B (en) | 2024-08-06 |
Family
ID=61084017
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711034034.2A Active CN107600426B (en) | 2017-10-30 | 2017-10-30 | Single-power-driven variable-pitch multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107600426B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108319282B (en) * | 2018-02-07 | 2020-11-24 | 衢州职业技术学院 | Control method and control device for multi-rotor aircraft |
| CN108275279A (en) * | 2018-04-10 | 2018-07-13 | 辽宁壮龙无人机科技有限公司 | UAV transmission components and UAV |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104859838A (en) * | 2015-06-03 | 2015-08-26 | 中恒天信（天津）航空科技有限公司 | Oil-driving multi-rotor unmanned flying platform |
| CN207360582U (en) * | 2017-10-30 | 2018-05-15 | 姬永超 | Single-power drives feather multi-rotor unmanned aerial vehicle |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752331A (en) * | 2016-04-26 | 2016-07-13 | 北京理工大学 | Single-internal combustion engine power multi-rotor wing unmanned aerial vehicle based on variable pitch control |
| CN107235155A (en) * | 2017-06-21 | 2017-10-10 | 桂艳春 | A kind of transmission device for high speed multirotor helicopter |
-
2017
- 2017-10-30 CN CN201711034034.2A patent/CN107600426B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104859838A (en) * | 2015-06-03 | 2015-08-26 | 中恒天信（天津）航空科技有限公司 | Oil-driving multi-rotor unmanned flying platform |
| CN207360582U (en) * | 2017-10-30 | 2018-05-15 | 姬永超 | Single-power drives feather multi-rotor unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107600426A (en) | 2018-01-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103381885B (en) | Multi-rotor aerocraft | |
| US20170327219A1 (en) | Vertical take-off and landing aircraft with hybrid power and method | |
| CN104176247A (en) | Four-rotor unmanned aerial vehicle with engine for directly driving rotor | |
| WO2006006311A1 (en) | Rapid air quantity generating and wind direction changing device and aircraft having the device mounted on side face of airframe | |
| CN102582832A (en) | Flapping-wing aircraft | |
| CN104859853A (en) | Six-rotor hybrid aircraft | |
| CN110979653A (en) | Three-steering-engine coaxial dual-rotor system and control strategy thereof | |
| CN105667780A (en) | Multi-rotor aircraft | |
| CN107600426B (en) | Single-power-driven variable-pitch multi-rotor unmanned aerial vehicle | |
| CN109383759A (en) | Aircraft based on flight attitude is adjusted to control plane | |
| CN206141823U (en) | Many rotors plant protection unmanned aerial vehicle | |
| CN208715474U (en) | A multi-rotor drone | |
| CN108382582B (en) | Electromechanical device capable of realizing conversion of flapping-fixing wing structure and aircraft | |
| CN119637133A (en) | Water-air cross-medium aircraft | |
| CN103803075A (en) | Solar gear-transmission disc type multi-rotor-wing aircraft | |
| CN207943169U (en) | A kind of four axis rolling rotor aircraft | |
| CN205440864U (en) | Unmanned helicopter of many rotors | |
| CN107054633B (en) | Practical miniature helicopter system | |
| CN109250095A (en) | A kind of VTOL fixed wing aircraft | |
| CN109850144A (en) | A kind of solar energy flapping wing bionic Aircraft | |
| CN113306713B (en) | Coaxial dual-rotor UAV based on parallelogram control rotor axis | |
| CN205524965U (en) | Multi -rotor aircraft | |
| CN213649894U (en) | Thrust vector tail sitting type vertical take-off and landing unmanned aerial vehicle | |
| CN207360582U (en) | Single-power drives feather multi-rotor unmanned aerial vehicle | |
| CN103803073A (en) | Fuel-driven bevel-gear-transmission disc type multi-rotor-wing aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |