CN205293073U - Oil moves and directly drives many rotor crafts - Google Patents
Oil moves and directly drives many rotor crafts Download PDFInfo
- Publication number
- CN205293073U CN205293073U CN201520861494.2U CN201520861494U CN205293073U CN 205293073 U CN205293073 U CN 205293073U CN 201520861494 U CN201520861494 U CN 201520861494U CN 205293073 U CN205293073 U CN 205293073U
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- combustion engine
- rotor
- internal combustion
- directly drives
- fuselage
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 84
- 230000000712 assembly Effects 0.000 claims description 31
- 238000000429 assembly Methods 0.000 claims description 31
- 239000003921 oil Substances 0.000 claims description 29
- 239000002828 fuel tank Substances 0.000 claims description 16
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 15
- 238000004891 communication Methods 0.000 claims description 14
- 238000012544 monitoring process Methods 0.000 claims description 10
- 239000010705 motor oil Substances 0.000 claims description 2
- 230000005540 biological transmission Effects 0.000 abstract description 7
- 230000005611 electricity Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000105 evaporative light scattering detection Methods 0.000 description 1
- 239000002803 fossil fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000003502 gasoline Substances 0.000 description 1
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- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
Abstract
The utility model belongs to many rotor crafts field relates to an oil moves and directly drives many rotor crafts, including fuselage, controller, rotor subassembly, the rotor subassembly includes rotor and the power unit who is used for driving the rotor, and is a plurality of the rotor subassembly respectively through the support arm with fuselage fixed connection, fixed mounting's effect is talked about for the rotor subassembly to the fuselage, the controller is used for controlling the state of flight of aircraft, power unit includes internal -combustion engine, steering wheel and oil tank, the oil tank with the internal -combustion engine passes through the oil circuit intercommunication, the steering wheel with controller electricity signal connection, the output shaft of internal -combustion engine with the rotor drive is connected, the utility model discloses the power of internal -combustion engine output directly transmits the rotor, does not have middle transmission mechanism, high transmission efficiency, and drive mechanism is simple, and the transmission is reliable and stable.
Description
Technical field
This utility model belongs to multi-rotor aerocraft field, and this utility model relates to a kind of oily moving and directly drives multi-rotor aerocraft.
Background technology
Multi-rotor aerocraft is the one of existing aircraft, and its primary structure can be divided into four parts: fuselage, undercarriage, controller, electronic rotor. The advantages such as it has maneuverability, be swift in response, autonomous flight, foolproof operation, all apply to some extent in dual-use field.
Tradition multi-rotor aerocraft adopts motor as power, and battery is powered, and the stored energy of unit cells is much smaller than Fossil fuels such as gasoline, so current many rotors ubiquity is short for cruising time, and the problem that load-carrying is little.
Existing oil moves many rotors and adopts varying pitch to control, and drive system is complicated, and transmission efficiency is low; Relying on the pitch simultaneously controlling multiple rotor change to control the attitude of aircraft, control complexity, reliability is poor; Mechanical structured member quantity is more, causes that aircraft bare weight is excessive, and loading capacity is limited.
Utility model content
In order to solve, existing electronic many rotors cruising time is short, load-carrying is little and the existing oil many rotors of dynamic varying pitch control problem complicated, poor reliability, and this utility model provides a kind of simple in construction, the oil-burning machine of dependable performance directly drives the multi-rotor aerocraft of rotor.
The technical scheme of this practicality is as follows:
A kind of oil is dynamic directly drives multi-rotor aerocraft, and including fuselage, controller, rotor assemblies, described rotor assemblies includes rotor and for driving the actuating unit of rotor, and multiple described rotor assemblies are connected respectively through support arm and described fuselage are fixing;
Described actuating unit includes internal combustion engine, steering wheel and fuel tank, described fuel tank and described internal combustion engine are by oil communication, and described steering wheel is connected with described I. C. engine oil gate control valve, described controller is connected with the described steering wheel signal of telecommunication, and the output shaft of described internal combustion engine drives with described rotor and is connected.
Described actuating unit includes internal combustion engine bracing frame, and described internal combustion engine bracing frame is fixing with described support arm to be connected, and the output shaft of described internal combustion engine is installed on described internal combustion engine bracing frame, and is connected with rotor driving.
Described actuating unit includes internal combustion engine mounting base, and described internal combustion engine mounting base is fixed on described support arm, and described internal combustion engine is fixed on described internal combustion engine mounting base; Described internal combustion engine bracing frame is fixed on described internal combustion engine mounting base.
The vertical axis at described fuselage center was set, first reference plane of described axis and rotor wing rotation planar central were set, the relative first reference plane deflection of output shaft of described internal combustion engine, deflection angle is the first angle, described first angle is 0��15 ��, the output shaft of described adjacent internal combustion engine is contrary relative to the first reference plane yawing moment, vertical first reference plane and the second reference plane being vertically arranged are set, described internal combustion engine output shaft deflects relative to the second reference plane, deflection angle is the second angle, and described second angle is-15��15 ��.
Described rotor wing rotation planar central line polygon axisymmetricly.
Described polygon is rectangle or regular hexagon.
Described fuel tank is arranged at described fuselage.
Described fuel tank is fixedly installed in each rotor assemblies respectively.
Described controller includes communication unit, navigation management unit, flight control units, electrically activates control unit, monitoring, alarming unit; Described flight control units respectively with described communication unit, navigation management unit, electrically activate control unit, monitoring, alarming unit and the steering wheel signal of telecommunication and be connected.
Described actuating unit also includes starting motor, and described startup motor drives described internal combustion engine start, electrically activates control unit and is connected with starting the motor signal of telecommunication.
Arranging power supply, described power supply is fixed on described fuselage, for powering to described controller and described rotor assemblies, exports 16v, 12v, 5v, 3.3v voltage.
Described aircraft also includes the undercarriage being arranged at below fuselage.
Described oil circuit, circuit are arranged in described support arm.
Beneficial effect
Oil provided by the utility model is dynamic directly drives multi-rotor aerocraft, including fuselage, undercarriage, controller, rotor assemblies, described rotor assemblies includes rotor and for driving the actuating unit of rotor, actuating unit includes internal combustion engine, steering wheel and fuel tank, described fuel tank and described internal combustion engine are by oil communication, to described internal combustion engine fuel feeding; Described steering wheel is connected with the modulator pressure regulator of described internal combustion engine by linkage, by controlling throttle size adjustment engine speed, described controller is connected with the described steering wheel signal of telecommunication, and controller drives linkage by steering wheel, and then regulates the throttle having internal combustion engine; The output shaft of described internal combustion engine drives with described rotor and is connected, and the power of internal combustion engine output is directly delivered to rotor, it does not have intermediate transmission mechanism, and transmission efficiency is high, and drive mechanism is simple, and stable transmission is reliable.
Accompanying drawing explanation
Fig. 1 is this utility model structural representation;
Fig. 2 is the partial enlarged drawing in I region in Fig. 1;
Fig. 3 is this utility model electric control schematic diagram;
Fig. 4 is this utility model rotor rectangle layout drawing;
Fig. 5 is this utility model rotor regular polygon shape layout drawing
Fig. 6 deflects schematic diagram with the first reference plane B for benchmark internal combustion engine output shaft;
Fig. 7 deflects schematic diagram with the second reference plane C for benchmark internal combustion engine output shaft.
In figure, 1 is fuselage, and 2 is undercarriage, and 3 is controller, 4 is rotor assemblies, and 11 is support arm, and 12 is brace, 41 is actuating unit, and 42 is rotor, and 411 is internal combustion engine, 412 is steering wheel, 413 is linkage, and 414 is steering wheel frame, and 415 is fuel tank, 416 is internal combustion engine mounting base, and 417 is internal combustion engine bracing frame.
Detailed description of the invention
In order to make the purpose of this utility model, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, this utility model is further elaborated. Should be appreciated that specific embodiment described herein is only in order to explain this utility model, be not used to limit this utility model.
As shown in Figure 1, the present embodiment directly drives multi-rotor aerocraft for a kind of oil is dynamic, including fuselage 1, undercarriage 2, controller 3 and many group rotor assemblies 4, except aircraft, the present embodiment arranges the remote control end coordinated with aircraft, and remote control end includes remote controller and earth station.
Fuselage 1 is ten octahedral structures, and fuselage 1 upper surface level, and fuselage 1 is used for installing controller 3 and fixing rotor assemblies 4.
Rotor assemblies 4 electrically connects with controller 3 respectively, rotor assemblies includes rotor 42 and for driving the actuating unit 41 of rotor 42, fuselage 1 arranges support arm 11, and support arm 11 is radially around being fixed on fuselage 1, and rotor assemblies 4 is connected respectively through support arm 11 is fixing with described fuselage 1.
The present embodiment rotor 42 center of rotation line polygon axisymmetricly. As shown in Figure 4, the present embodiment arranges 6 groups of rotor assemblies, and polygon is rectangle.
6 rotors 42 of rotor assemblies 4 are divided into 3 positive switch rotors and 3 reversion rotors, and turning to of adjacent rotor is contrary; As shown in Figure 4,6 rotors 42 are rectangle layout around the line being fixed on 1,6 rotor 42 center of rotation of fuselage radially, be respectively provided with 3 rotors 42 on rectangular two long limits, and the rotor 42 on two long limits is symmetricly set in fuselage 1 both sides. Rotor 42 center of rotation line is arranged as rectangle, reduces the space taken, and monnolithic case is similar to Automobile Transportation compartment, it is simple to transport.
The rotor assemblies 4 of fuselage 1 both sides is at a distance of 100cm, and every side arranges three groups of rotor assemblies 4, is arranged in a linear, and the same side adjacent rotor assembly 4 is apart from for 90cm.
As shown in Figure 6, the vertical axis L at the center of fuselage 1 was set, the axis of fuselage 1 and the first reference plane B at rotor wing rotation plane A center were set, the relative first reference plane B deflection of output shaft of internal combustion engine 411, being the first angle �� with the first reference plane B, described first angle �� is 0��15 ��, as it is shown in fig. 7, arrange vertical first reference plane B and the second reference plane C being vertically arranged, described internal combustion engine output shaft deflects with reference to flat C relative to second, is the second angle �� with described second reference plane C, and described second angle �� is-15 �㡫15 ��. the rotor 42 that fuel oil drives control in response speed slower, the output shaft of internal combustion engine 411 deflects respectively in the first reference plane B direction and the second reference plane C direction, the output shaft and the first reference plane B and the second reference plane C that make internal combustion engine 11 are angle, rotor 42 produces component respectively in vertical first reference plane B direction and vertical second reference plane C direction, add the rotor 42 horizontal force to fuselage 1, in being the increase in aircraft response speed on vertical first reference plane B direction and vertical second reference plane C direction, make aircraft flight direction, flight attitude regulation and control are more rapidly accurately.
In the present embodiment, overlook rotor 42 from body upper, rotate to be rotating forward counterclockwise, clockwise turn to reversion. The output shaft yawing moment of adjacent internal combustion engine 411 is contrary, and from fuselage to rotor direction, the output shaft one of the adjacent internal combustion engine 411 of the present embodiment deflects to the left, and another deflects to the right.Positive switch rotor rotates counterclockwise, and the anti-twisted force direction of generation is clockwise; Reversion rotor turns clockwise, and the anti-twisted force direction of generation is counterclockwise. Therefore produced by adjacent rotor, anti-twisted power can be cancelled out each other, and makes aircraft flight more stable.
Other embodiments of the present utility model are as it is shown in figure 5, the center of rotation line of 6 rotors 42 is the outside that regular polygon is arranged at fuselage 1.
As in figure 2 it is shown, actuating unit 41 includes internal combustion engine 411, internal combustion engine mounting base 416 and fuel tank 415, fuel tank 415 is fixed on fuselage 1, with internal combustion engine 411 by oil communication, is used for internal combustion engine 411 fuel feeding to rotor assemblies 4. Support arm 11 one end connects fuselage 1, internal combustion engine mounting base 416 is arranged at the other end of support arm 11, internal combustion engine 411 is fixed on internal combustion engine mounting base 416, and the output shaft of internal combustion engine 411 drives with rotor 42 and is connected, and internal combustion engine 411 is also connected with described controller 3 signal of telecommunication.
In the present embodiment, fuel tank 415 can also be fixedly installed on each rotor assemblies 4 respectively. Each independent fuel feeding of fuel tank 415 is to the internal combustion engine 411 of corresponding rotor assemblies 4.
Actuating unit 41 also sets up internal combustion engine bracing frame 417, described internal combustion engine bracing frame 417 is fixed on described internal combustion engine mounting base 416, the output shaft of described internal combustion engine 411 is fixed on described internal combustion engine bracing frame 417, and be connected with rotor 42 driving, internal combustion engine bracing frame 417 lower end is fixing with internal combustion engine mounting base 416 to be connected, upper end is fixing starts output shaft, is used for preventing output shaft jitter and shaking, and the rotation making rotor 42 is more stable.
Actuating unit 41 also sets up startup motor, starts motor and is arranged at internal combustion engine 411, drives internal combustion engine 411 to start.
Actuating unit 41 also sets up steering wheel 412 and steering wheel frame 414, and steering wheel 412 is fixed on steering wheel frame 414, and steering wheel frame 414 is connected with internal combustion engine bracing frame 417; The output shaft of steering wheel 412 is connected with linkage 413, and linkage 413 is connected with the modulator pressure regulator of internal combustion engine 411, it is achieved the steering wheel 412 control to electromotor 411.
The fuselage 1 of the present embodiment aircraft is arranged below undercarriage 2, support arm 11 is that an independent root is for fixing the bar of rotor assemblies 4, fuselage 1 also sets up brace 12, brace 12 is arranged at the lower section of support arm 11 in the present embodiment, brace 12 one end fixed landing gear 2, the other end is fixed on the position of the nearly rotor assemblies 4 of support arm 11. An independent support arm 11 fixes rotor assemblies 4, and stability is not enough, by the fixing rotor assemblies 4 of brace 12 auxiliary, especially strengthens the stability of rotor assemblies 4.
Support arm 11 is that tubular structure, oil circuit and circuit are arranged in support arm 11, and the oil circuit of the present embodiment and circuit are arranged in pipe, has the effect of protection oil circuit circuit.
As it is shown on figure 3, device includes communication unit, navigation management unit, flight control units and electrically activates control unit.
Communication unit connects flight control units and remote control end, for receiving the control data of remote control end, launches flight directive to flight control units, and returns flight state to remote control end;
Navigation management unit connects flight control units, is used for gathering sensing data and resolving navigational parameter, sends navigation data to flight control units;
Flight control units connects communication unit, electrically activates control unit and navigation management unit, receives the navigation data of navigation management unit and the flight directive of communication unit, calculates controlled quentity controlled variable according to navigation data and flight directive, allocates power control unit.
Flight control units connects steering wheel 412, and steering wheel 412 connects linkage 413, and linkage 413 connects the modulator pressure regulator of internal combustion engine 411, the output shaft rotation of steering wheel 412, linkage 413 is driven to swing, and then adjusting internal combustion engine 411 throttle, control internal combustion engine 411 rotating speed.
Electrically activate control unit and connect startup motor, control internal combustion engine 411 by the startup of control startup motor and start.
Monitoring, alarming unit includes oil mass detection alarm unit and electric quantity monitoring alarm unit, is used for detecting fuel tank 415 oil mass and electric quantity of power supply. When oil mass or electricity deficiency, oil mass monitoring means and electric quantity monitoring unit send monitoring information to flight control units, flight control units controls alarm unit and sends alarm, flight control units can pass through communication unit and send monitoring information to ground, in order to earth station understands the running status of aircraft in time.
Power supply is controller 3 and rotor assemblies 4 is powered, and exports 16v, 12v, 5v, 3.3v voltage. In the present embodiment, Power Management Unit output 16v voltage is to starting motor, and output 12v voltage to engine ignition, exports 5v voltage to steering wheel, exports 3.3v voltage to controller 3.
Rotor assemblies 4 arranges startup motor, starts motor connection and electrically activates control unit and internal combustion engine 411, electrically activates control unit and starts by starting motor control internal combustion engine 411.
This utility model structurally control structure is simple, it is provided with rational controller 3, the communication for information between remote controller and earth station and aircraft is realized by the controller 3 of the present embodiment, by flight control modules with electrically activate control unit and the steering wheel 412 that is arranged on internal combustion engine 411 realizes flight attitude control, when aircraft self-condition is not good, this practical information can monitor the oil mass electricity of aircraft, make prompting or alarm in time, originally it is that utility model has good stability, safe and reliable.
The above; it is only this utility model preferably detailed description of the invention; but protection domain of the present utility model is not limited thereto; any those familiar with the art is in the technical scope that this utility model discloses; the change that can readily occur in or replacement, all should be encompassed within protection domain of the present utility model. Therefore, protection domain of the present utility model should enclose with the protection of claim and be as the criterion.
Claims (10)
1. an oil moves and directly drives multi-rotor aerocraft, it is characterized in that, including fuselage, controller, rotor assemblies, described rotor assemblies includes rotor and for driving the actuating unit of rotor, and multiple described rotor assemblies are connected respectively through support arm and described fuselage are fixing;
Described actuating unit includes internal combustion engine, steering wheel and fuel tank, described fuel tank and described internal combustion engine are by oil communication, and described steering wheel is connected with described I. C. engine oil gate control valve, described controller is connected with the described steering wheel signal of telecommunication, and the output shaft of described internal combustion engine drives with described rotor and is connected.
2. a kind of oil according to claim 1 is dynamic directly drives multi-rotor aerocraft, it is characterized in that, described actuating unit includes internal combustion engine bracing frame, described internal combustion engine bracing frame is fixing with described support arm to be connected, the output shaft of described internal combustion engine is installed on described internal combustion engine bracing frame, and is connected with rotor driving.
3. a kind of oil according to claim 2 is dynamic directly drives multi-rotor aerocraft, it is characterised in that described actuating unit includes internal combustion engine mounting base, and described internal combustion engine mounting base is fixed on described support arm, and described internal combustion engine is fixed on described internal combustion engine mounting base; Described internal combustion engine bracing frame is fixed on described internal combustion engine mounting base.
4. a kind of oil according to claim 1 is dynamic directly drives multi-rotor aerocraft, it is characterized in that, the vertical axis at described fuselage center was set, first reference plane of described axis and rotor wing rotation planar central were set, the relative first reference plane deflection of output shaft of described internal combustion engine, deflection angle is the first angle, described first angle is 0��15 ��, the output shaft of described adjacent internal combustion engine is contrary relative to the first reference plane yawing moment, vertical first reference plane and the second reference plane being vertically arranged are set, described internal combustion engine output shaft deflects relative to the second reference plane, deflection angle is the second angle, described second angle is-15��15 ��.
5. a kind of oil according to claim 1 is dynamic directly drives multi-rotor aerocraft, it is characterised in that described rotor wing rotation planar central line polygon axisymmetricly.
6. a kind of oil according to claim 5 is dynamic directly drives multi-rotor aerocraft, it is characterised in that described polygon is rectangle or regular hexagon.
7. a kind of oil according to claim 1 to 6 any one moves and directly drives multi-rotor aerocraft, it is characterised in that described fuel tank is arranged at described fuselage.
8. a kind of oil according to claim 1 to 6 any one moves and directly drives multi-rotor aerocraft, it is characterised in that described fuel tank is fixedly installed in each rotor assemblies respectively.
9. a kind of oil according to claim 1 is dynamic directly drives multi-rotor aerocraft, it is characterised in that described controller includes communication unit, navigation management unit, flight control units, electrically activates control unit, monitoring, alarming unit; Described flight control units respectively with described communication unit, navigation management unit, electrically activate control unit, monitoring, alarming unit and the steering wheel signal of telecommunication and be connected.
10. a kind of oil according to claim 9 is dynamic directly drives multi-rotor aerocraft, it is characterised in that described actuating unit also includes starting motor, and described startup motor drives described internal combustion engine start, electrically activates control unit and is connected with starting the motor signal of telecommunication.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520861494.2U CN205293073U (en) | 2015-10-30 | 2015-10-30 | Oil moves and directly drives many rotor crafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520861494.2U CN205293073U (en) | 2015-10-30 | 2015-10-30 | Oil moves and directly drives many rotor crafts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205293073U true CN205293073U (en) | 2016-06-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520861494.2U Expired - Fee Related CN205293073U (en) | 2015-10-30 | 2015-10-30 | Oil moves and directly drives many rotor crafts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205293073U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043695A (en) * | 2016-06-28 | 2016-10-26 | 辽宁壮龙无人机科技有限公司 | Oil driven multi-rotor unmanned aerial vehicle fixed pitch variable speed system and control technique |
| CN106081132A (en) * | 2016-07-27 | 2016-11-09 | 辽宁壮龙无人机科技有限公司 | Fuel power many rotor wing unmanned aerial vehicles fuel feeding scheme |
| CN108622374A (en) * | 2017-03-22 | 2018-10-09 | 深圳常锋信息技术有限公司 | A kind of control method and device of unmanned plane |
| CN109484617A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of oblique pull cable wire and assembly and disassembly methods for the dynamic unmanned plane of oil |
| CN110494356A (en) * | 2017-04-12 | 2019-11-22 | 福特全球技术公司 | Multiple no-manned plane surface car jump start |
-
2015
- 2015-10-30 CN CN201520861494.2U patent/CN205293073U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043695A (en) * | 2016-06-28 | 2016-10-26 | 辽宁壮龙无人机科技有限公司 | Oil driven multi-rotor unmanned aerial vehicle fixed pitch variable speed system and control technique |
| CN106081132A (en) * | 2016-07-27 | 2016-11-09 | 辽宁壮龙无人机科技有限公司 | Fuel power many rotor wing unmanned aerial vehicles fuel feeding scheme |
| CN106081132B (en) * | 2016-07-27 | 2019-06-11 | 辽宁壮龙无人机科技有限公司 | Fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme |
| CN108622374A (en) * | 2017-03-22 | 2018-10-09 | 深圳常锋信息技术有限公司 | A kind of control method and device of unmanned plane |
| CN110494356A (en) * | 2017-04-12 | 2019-11-22 | 福特全球技术公司 | Multiple no-manned plane surface car jump start |
| CN110494356B (en) * | 2017-04-12 | 2023-08-29 | 福特全球技术公司 | Multi-unmanned aerial vehicle ground vehicle cross-over start |
| CN109484617A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of oblique pull cable wire and assembly and disassembly methods for the dynamic unmanned plane of oil |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220505 Address after: 518000 a1311, building 5, Shenzhen Bay science and technology ecological park, No. 26, Gaoxin South Ring Road, high tech Zone community, Yuehai street, Nanshan District, Shenzhen, Guangdong Patentee after: Shenzhen Lingyue Aviation Technology Co.,Ltd. Address before: 518000 third floor, building a, Jinguang science and Technology Park, No. 17-1, Pingxi South Road, Pingdi street, Longgang District, Shenzhen, Guangdong Province Patentee before: SHENZHEN CHANGFENG INFORMATION TECHNOLOGY Co.,Ltd. |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160608 |