CN203497176U - Unmanned helicopter - Google Patents
Unmanned helicopter Download PDFInfo
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- CN203497176U CN203497176U CN201320302740.1U CN201320302740U CN203497176U CN 203497176 U CN203497176 U CN 203497176U CN 201320302740 U CN201320302740 U CN 201320302740U CN 203497176 U CN203497176 U CN 203497176U
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- depopulated helicopter
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Abstract
The utility model relates to an unmanned helicopter which comprises a power system, a control system, a flight system and a transmission system, and a helicopter body used for carrying the power system, the control system, the flight system and the transmission system, and the flight system comprises a rotor head and four main rotors fixed on the rotor head. The unmanned helicopter provided by the utility model is large in lift force by adopting a layout manner of the four main rotors, thereby improving the load performance.
Description
Technical field
The utility model relates to mechanical field, relates in particular to a kind of depopulated helicopter.
Background technology
Because unmanned plane has, can adapt to complicated harsh environment, therefore needs personnel do not drive, can not cause the great advantages of personal casualty loss, have obtained application more and more widely.Unmanned plane technology has all been used in the fields such as remote sensing observing and controlling at present,, the mapping of taking photo by plane, environment scouting.
Along with increasing of application, unmanned plane technology is more and more hotter, and unmanned machine class is tending towards variation.Generally speaking, unmanned plane comprises power system, control system, flight system and the transmission system that fuselage and fuselage are carrying.Current, the flight system of typical unmanned plane adopts the structure of two main rotors, and adopts balance wing to control the balance of unmanned plane.And the general use of unmanned plane is that aviation aluminum is made side plate 10 body parts such as grade now, makes the weight of unmanned plane receive restriction.
Current, the technology of unmanned plane is perfect not enough, exists various deficiencies, such as preponderance, load capacity deficiency etc.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of depopulated helicopter, improves load capacity.
For solving the problems of the technologies described above, the utility model proposes a kind of depopulated helicopter, comprise power system, control system, flight system and transmission system, and the fuselage that carries described power system, control system, flight system and transmission system, described flight system comprises a rotor head and is fixed on four main rotors on described rotor head.
Further, above-mentioned depopulated helicopter also can have following characteristics, and described four main rotors are positioned at same plane, and described plane is perpendicular to described rotor head, and described four main rotors are symmetrical arranged between two, between adjacent two main rotors, all become 90 degree angles.
Further, above-mentioned depopulated helicopter also can have following characteristics, and described rotor head is provided with four main slurry folders, and described four main rotors are clamping on described rotor head by a described main slurry respectively.
Further, above-mentioned depopulated helicopter also can have following characteristics, on described rotor head, is provided with slide block, and described slide block is respectively provided with a projecting block on the position corresponding with described four main rotors, and described projecting block is connected with described main slurry folder by fixed connecting rod.
Further, above-mentioned depopulated helicopter also can have following characteristics, and described fixed connecting rod is length-adjustable fixed connecting rod.
Further, above-mentioned depopulated helicopter also can have following characteristics, and described power system comprises driving engine, and the upper spacer of described driving engine and described fuselage is fixed by two hanging beams.
Further, above-mentioned depopulated helicopter also can have following characteristics, and described power system is also included as the heat abstractor of described engine radiating, and the air outlet of the air-out passage of described heat abstractor partly covers the cylinder of described driving engine.
Further, above-mentioned depopulated helicopter also can have following characteristics, and described fan also comprises flabellum, and described flabellum is for lengthening flabellum.
Further, above-mentioned depopulated helicopter also can have following characteristics, and described fuselage comprises upper spacer and lower clapboard, and described lower clapboard is for lengthening thickening dividing plate.
Further, above-mentioned depopulated helicopter also can have following characteristics, and described transmission system comprises main shaft, on described main shaft, unilateral bearing is installed.
Depopulated helicopter of the present utility model, the layout type of four main rotors of employing, lift is large, thereby has improved load performance.
Accompanying drawing explanation
Fig. 1 is the lateral plan of depopulated helicopter in the utility model embodiment;
Fig. 2 is the front elevation of depopulated helicopter in the utility model embodiment;
Fig. 3 is the partial enlarged drawing of the main rotor part of depopulated helicopter in the utility model embodiment;
Fig. 4 is the partial enlarged drawing of the engine section of depopulated helicopter in the utility model embodiment;
Fig. 5 is the afterbody partial enlarged drawing of depopulated helicopter in the utility model embodiment;
Fig. 6 is the structured flowchart of the control system of depopulated helicopter in the utility model embodiment;
Fig. 7 is the system construction drawing of unmanned lift-off platform in the utility model embodiment;
In accompanying drawing, the list of parts of each label representative is as follows:
1, main rotor, 2, rotor head, 3, battery case, 4, freeing pipe, 5, tail pipe, 6, GPS module, 7, tail-rotor, 8, shoe, 9, fuel tank, 10, side plate, 11, alighting gear, 12, air filter, 13, airborne equipment, 14, load support seat, 15, change speed gear box, 16, start head, 17, driving engine, 18, fan housting, 19, main shaft, 20, swash plate, 21, main shaft limiting card, 22, magneto generator, 23, power-transfer clutch, 24, synchronous pulley, 25, tail driving band, 26, coda wave case, 27, tail-rotor folder, 28, tail slide block shift sleeve structure.
The specific embodiment
Below in conjunction with accompanying drawing, principle of the present utility model and feature are described, example, only for explaining the utility model, is not intended to limit scope of the present utility model.
In the utility model embodiment, depopulated helicopter comprises power system, control system, flight system and transmission system, and the fuselage of carrying power system, control system, flight system and transmission system.
Fig. 1 is the lateral plan of depopulated helicopter in the utility model embodiment.
In the present embodiment, the fuselage of depopulated helicopter is comprised of upper spacer, lower clapboard, two of left and right side plate 10, alighting gear 11, tail pipe 5 etc.Fuselage plays the function of other parts of carrying aircraft, and the left and right sides upper spacer of fuselage, lower clapboard, two of left and right side plate 10, tail pipe 5 are made by carbon fibre material, have reduced the weight of depopulated helicopter.Load support seat 14 is positioned at the top that keeps left of two side plates 10 in left and right.On left side board, right side board, be respectively provided with 14, two load support seats 14 of two load support seats and be arranged symmetrically with, load support seat 14 has shock absorption device above, and load airborne equipment 13 according to demand.As shown in Figure 1, on depopulated helicopter, there is battery case 3, for power supply.
Referring to Fig. 1 and Fig. 3, in the present embodiment, the power system of depopulated helicopter be take driving engine 17 as main, driving engine 17 is fixed on front fuselage, between left side board and right side board, driving engine 17 is held fixing below by lower clapboard, driving engine 17 is fixed by two hanging beams with upper spacer above, and aircraft vibrations can effectively be alleviated near the center of gravity of airplane in driving engine 17 fixed positions.Driving engine 17 discharge capacities increase, and corresponding vibrations can aggravation, and depopulated helicopter of the present utility model adopts two hanging beams stationary engine 17 of slinging, and can effectively reduce vibrations.
Referring to Fig. 4, driving engine 17 is up provided with magneto generator 22, fan, power-transfer clutch 23, synchronous pulley 24 successively, start 16.Fan housting 18 exhausr ports are concentrated the cylinder of driving engine 17 are blown to heat radiation, and fan coordinates coordination more with the performance between fan housting 18, have increased the degree of utilization to drying, and can make driving engine 17 better play effectiveness.
The flabellum of fan has carried out diameter and has added long process, can produce larger wind.Fan housting 18 the right and lefts have the passage of two air-out, and passage includes ventilation inlet and air outlet, and air outlet covers the cylinder of driving engine 17 (not covering completely) and concentrates wind-force to driving engine 17 cylinder coolings.
Power system also comprises freeing pipe 4 and fuel tank 9, air filter 12, and freeing pipe 4 is connected by being flexible coupling with the exhausr port of driving engine 17, and not only exhaust is smooth and easy, also driving engine 17 is eliminated the noise, and has increased effective utilization of energy.In the present embodiment, driving engine 17 adopts large discharge capacity engine petrol, and for example discharge capacity can be 110cc(Cubic Centimeter, cm3), this can be so that the power of depopulated helicopter be more sufficient.
Magneto generator 22 is fixed on driving engine 17, is used for powering to light-up plug.Driving engine 17 is up fan, is fixed on engine shaft, with driving engine 17, rotates, and fan is used for to driving engine 17 heat radiations.Piece connection mode is got rid of in power-transfer clutch 23 employings, gets rid of between piece and connects with spring, and power-transfer clutch 23 is followed driving engine 17 and rotated, and produces centnifugal force in rotation process, gets rid of piece and throws away and the rotation of clutch cap laminating drive driving device.Synchronous pulley 24 is positioned at clutch cap top, is connected drives change speed gear box 15 drivings device to work by Timing Belt with change speed gear box 15 synchronous pulleys 24.Fan, power-transfer clutch 23, synchronous pulley 24 are fixed on driving engine 17 by concentric shafts, start 16 and are fixed on concentric shafts upper end, are used for the interface of start the engine 17.
Referring to Fig. 1, Fig. 2 and Fig. 3, in the present embodiment, the transmission system of depopulated helicopter comprises change speed gear box 15, afterbody transmission, afterbody transmission is comprised of tail driving band 25, coda wave case power wheel, change speed gear box 15 rear end power wheels, tail driving band 25 and coda wave case 26 are as shown in Figure 5, coda wave case power wheel is positioned at coda wave case 26, and change speed gear box 15 rear end power wheels are positioned at tail pipe 5 and change speed gear box 15 combinations.Change speed gear box 15 comprises variable gear, and there is gear oil variable gear the inside.Change speed gear box 15 is positioned at driving engine 17 back upper places, and change speed gear box 15 is fixed on upper spacer.Change speed gear box 15 produces associated by synchronous pulley 24 and Timing Belt and driving engine 17, change speed gear box 15 has two-stage variable gear.Variable gear is for changing the rotating speed that driving engine 17 transmissions are come.Gear and the generation of main shaft tail driving device by mutual interlock contact, and drive the rotation of main rotor 1 and tail-rotor 7.Change speed gear box 15 reduced and main shaft 19 between kinetic energy loss.On the main shaft 19 of change speed gear box 15, unilateral bearing is housed, is contained on synchronous pulley 24 and compares with unilateral bearing, the present invention is when driving engine 17 stops, and 19 needs self of main shaft rotate, and needn't rotate by driven gear simultaneously.On unilateral bearing and main shaft 19, have groove, groove is combined with mace, and unilateral bearing is synchronizeed and rotated towards correct direction together with main shaft 19, can prevent like this because being subject to aerodynamic force to affect contrarotation.
The increase of change speed gear box 15 driving efficiencys, can promote aircraft flight energy utilization efficiency.In addition, change speed gear box 15 resistant material manufacture, appearance is through processing, and taken into full account it and born that fuel tank 9 superchargings are vibrated with driving engine 17 and the stress that brings.
Referring to Fig. 1 and Fig. 5, in the present embodiment, the flight system of depopulated helicopter comprises rotor head 2 and main rotor 1.
The flight system of depopulated helicopter adopts the layout type of four main rotors, that is to say, the flight system of depopulated helicopter comprises four main rotors, than two main rotors of existing unmanned plane, has promoted the lift of aircraft.These four main rotors are fixed on rotor head 2.As shown in fig. 1, main rotor 1 is fixed on rotor head 2 by main oar folder.Main rotor 1 and tail-rotor 7 are controlled turning to, climb, rolling of aircraft.
Four main rotors are positioned at same plane, and this plane is perpendicular to rotor head 2, and these four main rotors are symmetrical arranged between two, between adjacent two main rotors, all become 90 degree angles.
While rotating due to four main rotors to the downward application force of air, the antagonistic force that air can make progress to main rotor simultaneously, this antagonistic force is exactly the lift of aircraft, the power that four main rotors are subject to is greater than the power that two main rotors are subject to, thereby depopulated helicopter of the present utility model is than the unmanned plane of two main rotors of existing unmanned plane, promote the lift of aircraft, thereby improved load capacity.
The aerofoil profile of main rotor is the pattern that is close to plane below, walks arc above.According to Bai Nuli principle, the faster pressure of flow velocity is less, and such design has promoted the lift of aircraft.Main rotor 1 adopts the advanced composite materials such as carbon fiber, hard polyurethane foams and epoxy resin to make, have lightweight, intensity is high, corrosion stability and the advantage such as durability is strong.Depopulated helicopter of the present utility model has four main rotors, has three distances, has increased the operability of unmanned lift-off platform, and can strengthen its flexibility of operation by bulb, bulb button, ball head connecting rod etc. are installed.At main rotor 1 rear side, vertical swash plate track is installed, thereby swash plate track mixes control swash plate 20 at vertical range steering wheel, reaches the object of controlling unmanned lift-off platform.The adjustable positive and negative oar motion of main rotor 1, can not depart from center line.
On rotor head 2, be provided with four main slurry folders, four main rotors 1 are clamping on rotor head 2 by a main slurry respectively.On rotor head 2, be provided with slide block, this slide block is respectively provided with a projecting block on the position corresponding with four main rotors, and projecting block is connected with main slurry folder by fixed connecting rod.This fixed connecting rod is length-adjustable fixed connecting rod, to allow four main rotors in same level by controlling length.Slide block is connected with four main rotor folders the variation of controlling main rotor pitch by fixed connecting rod, with this, reaches the rolling etc. of climbing of controlling aircraft.
Referring to Fig. 1, rotor head 2 comprises main shaft limiting card 21, swash plate 20, slide block, rotor centre mount.Swash plate 20 is for driving the variation of pitch.
Main shaft limiting card 21 is controlled swash plate 20 and is moved up and down amplitude, and the distance up and down that swash plate 20 is connected with steering wheel by connecting rod by different azimuth swings the variation of controlling main rotor pitch.The fixing main oar folder of rotor centre mount, is enclosed within on main shaft 19.
Referring to Fig. 5, in the present embodiment, the flight system of depopulated helicopter also comprises tailing axle, tail-rotor centre mount, tail-rotor folder 27, tail-rotor 7, afterbody slide block, shoe 8, tail sliding sleeve, coda wave case 26.Tail-rotor 7 is fixed on the transverse axis of fuselage tail pipe 5 rear ends, and afterbody power wheel produces associated by tail driving band 25 with change speed gear box 15.Tail-rotor 7 adopts the advanced composite material hot settings such as carbon fiber to complete, and has lightweight, intensity advantages of higher.Fuselage is connected with tail-rotor 7 by tail pipe 5, and tail pipe 5 inside are Timing Belt, and Timing Belt is connected to tail-rotor 7 from change speed gear box 15, drives tail-rotor 7 operations.
Tail power wheel and other caudal components are all fixed on tailing axle, and tail-rotor centre mount is enclosed within on tailing axle fixedly tail-rotor folder 27, by connecting rod, is connected with afterbody slide block, sliding bush apparatus.Tail slide block shift sleeve structure 28 mutually combination is connected with steering wheel by connecting rod, drives main oar folder to produce pitch and changes.Shoe 8 shields, and prevents that tail-rotor 7 from getting to ground (in particular cases).Tail power wheel is fixed on tailing axle in coda wave case 26, is connected to produce afterbody and rotate desired rate by tail driving band 25 with change speed gear box 15 rear end power wheels.
Referring to Fig. 1 and Fig. 6, in the present embodiment, the control system of depopulated helicopter can comprise and flies to control box and radio station.Fly to control box and be arranged on after change speed gear box 15, above tail pipe 5, radio station is fixed on the left side board of fuselage.Fly to control box the inside equipment such as flying to control plate, GPS module 6, ultrasonic range finder, magnetometer, steering wheel, steering wheel plate, emitter receptor, gyroscope, airborne equipment power supply (not shown) is housed.Wherein, steering wheel comprises front four steering wheels and tail-rotor steering wheel.As seen from Figure 6, radio station, magnetometer, steering wheel plate, emitter receptor, ultrasonic range finder respectively with fly to control plate and be connected, GPS module 6 is arranged at and flies to control on plate, tail-rotor steering wheel is connected with steering wheel plate by gyroscope, front four steering wheels are connected with steering wheel plate.Ultrasonic range finder is a kind of sonar equipment.Flying to control box and these devices of radio station makes aircraft can carry out autonomous flight completely.
Flying to control plate is aircraft flight control circuit board, comprises various chips on circuit card, and the various signals that transmit by sensor send instruction and control aircraft flight.Radio station is data transmission radio station, the instruction of transmitting by satellite receiver.GPS module 6 is Plane location, and ultrasonic range finder carrys out detection range location aircraft coordinate with super sonic.Steering wheel is connected with tail-rotor 7 with main rotor 1 by connecting rod, and the variation by steering wheel arm drives pitch to change.Steering wheel plate is steering wheel fixedly.Gyroscope feeds back to aircraft flight attitude to fly to control plate, then flies to control plate and sends instruction adjustment flight attitude.Airborne equipment power supply is equipment power supply.
Can determine by GPS module 6, sonar equipment and magnetometer the three-dimensional coordinate of depopulated helicopter, these signals all input to and fly to control plate and carry out computing and be transferred to steering wheel plate, control the operation of 5 steering wheels, thereby reach, control the object that depopulated helicopter is carried out aerial mission.Wherein steering wheel plate is exported a road signal and is controlled tail-rotor 7 operations to gyroscope, keeps the stability of tail-rotor 7.Fly to control kernel software and comprise and run on the embedded core firmware program that flies to control on plate, can realize the utility functions such as data fusion, attitude algorithm, Navigation Control, parameter adjustment, course line are uploaded, standard course line, PID control, camera control, cradle head control, target lock-on, extraordinary circumstances processing, simulated flight.
Depopulated helicopter of the present utility model adopts 2.4G controlled in wireless to strengthen system, can automatically regulate the original pitching of aircraft, rolling and driftage input; Taking to optimize airline operation comes by a launch site and known threat; Low latitude, be close to topographic profile and fly to avoid being detected; Use a kind of automatic detection system that industrial computer is control core of take based on pci bus, system, by automatically gathering, batch differentiate, analyze to combination governor input analog stimulus and to feedback signal, has realized the automatic detection to regulating control.
Fig. 7 is the system construction drawing of unmanned lift-off platform in the utility model embodiment.
The electromagnetic compatibility of depopulated helicopter of the present utility model meets the related request of GJB.This unmanned lift-off platform flight control unit and communication facilities are three kinds altogether, and all devices all carries antenna, and electromagnetic Compatibility Design has guaranteed that between various device, working stability is reliable.The EMC Design of depopulated helicopter of the present utility model is divided into flight control, remote control distributor and radio communication.Wherein, the working frequency range of major equipment is as shown in table 1.
The working frequency range table of table 1 depopulated helicopter major equipment
| Sequence number | Device name | Working frequency range |
| 1 | Data transmission | 900MHz | |
| 2 | Telecommand equipment | 2.4G | |
| 3 | Wireless communication system | 400MHz is to 430MHz |
The overall mass of depopulated helicopter of the present utility model (deadweight) M
cpressing formula (1) calculates:
In formula (1), N
0for for estimating whole assembly quantity (division of assembly can be made by oneself by designer according to actual conditions) of complete machine curb mass, M
cfor complete machine curb mass (unit is a kilogram kg)
Complete machine height of center of mass Hg0 presses formula (2) and calculates:
In formula (2), Z
@0for each parts height of center of mass (unit is millimeter mm).
In an instantiation, the leading indicator of depopulated helicopter of the present utility model is as follows:
(1) technical index:
Oad (length) is 2700mm * 780mm * 780mm;
Main rotor diameter: 2140mm;
Climbing speed: 1m/s;
Max level speed: 30km/h;
Practical ceiling: 2000m;
Cruise duration: 1h;
Oil consumption: 5L/h.
(2) communication distance
Adopt remote controller to control flight, transmission distance≤1km;
Adopt data transmission radio station to control flight, transmission distance is≤10km;
(3) compatible with environment
Environment takes off: earth's surface wind-force is in 3-4 level;
Adapt to weather: light rain, slight snow;
Working relative humidity: 95%RH(is when ambient temperature is 25 ℃);
Operating altitude :≤1000m.
(4) power supply
Equipment operating voltage: DC7.4V-8.4V;
Steering wheel operating voltage: DC6.0V-7.0V;
Remote controller operating voltage: DC9.0V-11.0V;
Data transmission radio station operating voltage: AC220V;
Actuator operating voltage: DC12V.
(5) ground station's index
(1) remote controller
A) frequency of operation: 2.4GHz;
B) outdoor visual range: maximum can reach 1km;
C) size (mm): 210 * 200 * 100(length * wide * height);
D) weight (g): 820(is not containing battery).
(2) data transmission radio station
A) frequency of operation: 902-928MHz;
B) interface data communication speed: 10-230,400bps (comprising nonstandard baud rate);
C) radio frequency communication speed: 10,000bps;
D) input impedance: 50 Europe, overbalance mode;
E) open air/less radio-frequency visual range: maximum can reach 10km;
F) size (mm): 70 * 140 * 29(length * wide * height);
G) weight (g): 200.
Depopulated helicopter of the present utility model, the layout type of four main rotors of employing, lift is large, thereby has improved load performance.In addition, depopulated helicopter of the present utility model also tool has the following advantages: flight attitude is steady, and wind loading rating is strong; Flight altitude control precision is high, flying speed wide ranges; Gps satellite autonomous navigation flight, flight operation automation, simplification, intelligent degree are high; Adopt large free air capacity driving engine, power foot; Adopt carbon fibre material to make fuselage, own wt is light; The load capacity variation of finishing the work greatly.
The foregoing is only preferred embodiment of the present utility model, not in order to limit the utility model, all within spirit of the present utility model and principle, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (10)
1. a depopulated helicopter, comprise power system, control system, flight system and transmission system, and the fuselage that carries described power system, control system, flight system and transmission system, it is characterized in that, described flight system comprises a rotor head and is fixed on four main rotors on described rotor head.
2. depopulated helicopter according to claim 1, is characterized in that, described four main rotors are positioned at same plane, and described plane is perpendicular to described rotor head, and described four main rotors are symmetrical arranged between two, between adjacent two main rotors, all become 90 degree angles.
3. depopulated helicopter according to claim 1, is characterized in that, described rotor head is provided with four main slurry folders, and described four main rotors are clamping on described rotor head by a described main slurry respectively.
4. depopulated helicopter according to claim 3, it is characterized in that, on described rotor head, be provided with slide block, described slide block is respectively provided with a projecting block on the position corresponding with described four main rotors, and described projecting block is connected with described main slurry folder by fixed connecting rod.
5. depopulated helicopter according to claim 4, is characterized in that, described fixed connecting rod is length-adjustable fixed connecting rod.
6. depopulated helicopter according to claim 1, is characterized in that, described power system comprises driving engine, and the upper spacer of described driving engine and described fuselage is fixed by two hanging beams.
7. depopulated helicopter according to claim 6, is characterized in that, described power system is also included as the heat abstractor of described engine radiating, and the air outlet of the air-out passage of described heat abstractor partly covers the cylinder of described driving engine.
8. depopulated helicopter according to claim 7, is characterized in that, described fan also comprises flabellum, and described flabellum is for lengthening flabellum.
9. depopulated helicopter according to claim 1, is characterized in that, described fuselage comprises upper spacer and lower clapboard, and described lower clapboard is for lengthening thickening dividing plate.
10. depopulated helicopter according to claim 1, is characterized in that, described transmission system comprises main shaft, on described main shaft, unilateral bearing is installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320302740.1U CN203497176U (en) | 2013-05-29 | 2013-05-29 | Unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320302740.1U CN203497176U (en) | 2013-05-29 | 2013-05-29 | Unmanned helicopter |
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| CN203497176U true CN203497176U (en) | 2014-03-26 |
Family
ID=50328175
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| CN201320302740.1U Expired - Fee Related CN203497176U (en) | 2013-05-29 | 2013-05-29 | Unmanned helicopter |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103912418A (en) * | 2014-04-24 | 2014-07-09 | 四川测绘地理信息局测绘技术服务中心 | Extended-range unmanned aerial vehicle with novel air cleaner |
| CN104163242A (en) * | 2014-08-18 | 2014-11-26 | 国网湖北电力中超建设管理公司 | Three-blade fixture of multi-rotor-wing aircraft |
| TWI809614B (en) * | 2021-11-02 | 2023-07-21 | 大陸商廣州昂寶電子有限公司 | UAV control method and system and remote controller for remote control of UAV |
-
2013
- 2013-05-29 CN CN201320302740.1U patent/CN203497176U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103912418A (en) * | 2014-04-24 | 2014-07-09 | 四川测绘地理信息局测绘技术服务中心 | Extended-range unmanned aerial vehicle with novel air cleaner |
| CN104163242A (en) * | 2014-08-18 | 2014-11-26 | 国网湖北电力中超建设管理公司 | Three-blade fixture of multi-rotor-wing aircraft |
| CN104163242B (en) * | 2014-08-18 | 2016-09-14 | 国网湖北电力中超建设管理公司 | A kind of multi-rotor aerocraft SANYE oar fixture |
| TWI809614B (en) * | 2021-11-02 | 2023-07-21 | 大陸商廣州昂寶電子有限公司 | UAV control method and system and remote controller for remote control of UAV |
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Granted publication date: 20140326 |