CN207466966U - A kind of dynamic displacement quadrotor unmanned plane of oil - Google Patents
A kind of dynamic displacement quadrotor unmanned plane of oil Download PDFInfo
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- CN207466966U CN207466966U CN201721551492.9U CN201721551492U CN207466966U CN 207466966 U CN207466966 U CN 207466966U CN 201721551492 U CN201721551492 U CN 201721551492U CN 207466966 U CN207466966 U CN 207466966U
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Abstract
The utility model discloses a kind of oil to move displacement quadrotor unmanned plane, including：Body；Power rotor system, it includes two the first power rotor assemblies and two the second power rotor assemblies, using the crosspoint of the supporting rod as symmetric points, described two first power rotor assemblies symmetrically set up separately in two ends of the supporting rod, described two second power rotor assemblies symmetrically set up separately in remaining two ends of the supporting rod, the first power rotor assembly and the second power rotor assembly include being fixed by the bracket the driving mechanism on the supporting rod, the transmission mechanism being sequentially connected with the driving mechanism and the pulp distance varying mechanism and rotor mechanism that are arranged on above the transmission mechanism.The dynamic displacement quadrotor unmanned plane of oil provided by the utility model solves the problems such as conventional electronic multi-rotor unmanned aerial vehicle load-carrying is small, and the short wind resistance of endurance is poor, while solves a single engine vibrations greatly, and transmission accuracy is poor, and overall structure is simple, convenient for safeguarding.
Description
Technical field
The utility model is related to unmanned plane during flying device technical fields, and more specifically, the utility model is related to a kind of oil is dynamic
Displacement quadrotor unmanned plane.
Background technology
With the continuous development of unmanned plane industry, unmanned plane is applied in a variety of different fields, market pair both domestic and external
Also constantly increasing, while higher requirement is proposed for the continuation of the journey of unmanned plane and load-carrying again in unmanned plane demand.It is existing
Some unmanned plane majorities as power, are flown using battery by improving motor speed, the energy density and electricity of battery
The driving force of machine seriously limits the load of aircraft, and it is more narrow to be allowed to application field.
Chinese patent CN 105270619A disclose " a kind of dynamic displacement quadrotor unmanned plane of oil ", which includes power
System-transmission system, rotor-steerable system and machine frame system, rotor-steerable system, dynamical system-transmission system are all solid
It is scheduled on machine frame system.The utility model mainly solves conventional electronic more rotor load are small, endurance is short and wind resistance is poor etc.
Problem and pure helicopter are due to mechanical structure, structural dynamic characteristics, flight dynamics characteristic, aerodynamic characteristic and flight
The problems such as buying, the operation and maintenance that control system is complicated and brings are of high cost, and working service technical threshold is high.But the invention
In power sub-system with drive subsystem by the synchronous band connection of drive subsystem, when power sub-system and drive subsystem
Between synchronous belt tension when, then the power loss of unmanned plane is larger；Particularly flame-out landing, power sub-system and transmission subsystem
Synchronous belt pine excessively and easily skidding between system, can damage unmanned plane.
Utility model content
One purpose of the utility model is to solve at least the above, and provide the advantages of at least will be described later.
There are one purpose there is provided a kind of dynamic displacement quadrotor unmanned plane of oil, this oil moves displacement four and revolves the utility model
Wing unmanned plane individually provides power source with engine using four aviations to each rotor mechanism, solves conventional electronic more rotors
Unmanned plane load-carrying is small, and the short wind resistance of endurance is poor, while solves the problems such as a single engine vibrations are big, and transmission accuracy is poor, whole to tie
Structure installation is simple, convenient for safeguarding.
To achieve these goals, the utility model provides a kind of dynamic displacement quadrotor unmanned plane of oil, including：
Body, with cross-shaped supporting rod；
Power rotor system, including two the first power rotor assemblies and two the second power rotor assemblies, with described
The crosspoint of supporting rod is symmetric points, and described two first power rotor assemblies symmetrically set up separately at two ends of the supporting rod
Portion, described two second power rotor assemblies symmetrically set up separately in remaining two ends of the supporting rod, first power
Rotor assembly and the second power rotor assembly include being fixed by the bracket driving mechanism and institute on the supporting rod
The pulp distance varying mechanism and rotor mechanism stated the transmission mechanism of driving mechanism drive connection and be arranged on above the transmission mechanism,
For fixing propeller, the pulp distance varying mechanism with the rotor mechanism connect and for changing the spiral shell rotor mechanism
Revolve the rotation angle of attack of paddle；The driving mechanism of the first power rotor assembly drives the gyroplane of the first power rotor assembly
Structure carries out the rotation in a direction, and the driving mechanism of the second power rotor assembly drives the second power rotor assembly
Rotor mechanism progress rotates in the opposite direction with a side；
Wherein, the driving mechanism of the first power rotor assembly and the driving mechanism of the second power rotor assembly are equal
For aviation engine.
Preferably, the oil is moved in displacement quadrotor unmanned plane, the transmission mechanism of the first power rotor assembly
Include the connection being fixedly connected by screw with the aviation with engine with the transmission mechanism of the second power rotor assembly
Axis device, the one-way clutch being fixedly connected with the shaft coupling, the first order being connected by input shaft with the one-way clutch
Deceleration member and the second level deceleration member with first order deceleration member rotation connection；
The first order deceleration member of transmission mechanism in the first power rotor assembly slows down for three spur gear of the first order
Machine, the first order deceleration member of the transport mechanism in the second power rotor assembly are two spur gear speed reducer of the first order, institute
Slow down the second level for stating the transmission mechanism in the first power rotor assembly and the transport mechanism in the second power rotor assembly
Component is second level bevel gear reducing mechanism.
Preferably, the oil is moved in displacement quadrotor unmanned plane, the pulp distance varying mechanism includes being fixed on described the
First connecting rod, one end and the institute that steering engine, lower end on two level bevel gear reducing mechanism are flexibly connected with the output terminal of the steering engine
State first connecting rod upper end flexible connection and be set in outside the output shaft of the second level bevel gear reducing mechanism displacement rocking bar,
Upper end is flexibly connected with the displacement rocking bar and lower end is connect with the second level bevel gear reducing mechanism displacement support arm is arranged
The sliding shoe that is connect on the output shaft of the second level bevel gear reducing mechanism and with the displacement rocking bar is set in described
Pushing block and lower end on the output shaft of two level bevel gear reducing mechanism and above the sliding shoe are connect with the pushing block
And upper end and the second connecting rod of the paddle folder connection in the rotor mechanism, the first connecting rod are located at respectively with the displacement support arm
The both sides of the output shaft of the second level bevel gear reducing mechanism.
Preferably, the oil is moved in displacement quadrotor unmanned plane, it further includes：
Controller is arranged on the body, and the controller and the aviation are with starting mechatronics.
Preferably, the oil is moved in displacement quadrotor unmanned plane, the three spur gear speed reducer of the first order includes three
A first spur gear, one of them first spur gear are used to commutate.
Preferably, the oil is moved in displacement quadrotor unmanned plane, and the two spur gear deceleration mechanism of the first order includes
Two the second spur gears, one of them second spur gear are used to commutate.
The utility model includes at least following advantageous effect：
1st, the dynamic displacement quadrotor unmanned aerial vehicle design of oil described in the utility model is reasonable, and overall structure is simple, and uses
Long lifespan.
2nd, in the dynamic displacement quadrotor unmanned plane of oil described in the utility model aviation engine by way of axis transmission
Power is transmitted into rotor mechanism, and the process of axis transmission, the fast response time of rotor mechanism, power loss are small.
3rd, the dynamic displacement quadrotor unmanned plane of oil described in the utility model is individually given each by four aviations with engine
Rotor mechanism provides power source, solves that conventional electronic multi-rotor unmanned aerial vehicle load-carrying is small, and the short wind resistance of endurance is poor, while solves list
The problems such as platform engine vibration is big, and transmission accuracy is poor, overall structure installation is simple, convenient for safeguarding.
4th, in the dynamic displacement quadrotor unmanned plane of oil described in the utility model each rotor system by a single engine into
Action power drive, pitch-changing mechanism change the propeller angle of attack, make its power surplus sufficient, overcome close by the energy of dynamo battery
Spend a series of problems such as the low caused aircraft flight time is short, and load is light.
The dynamic displacement quadrotor unmanned plane of oil described in the utility model, the further advantage, target and feature of the utility model
Part is illustrated to embody by following, part also by by the research to the utility model and practice and the technology for this field
Personnel are understood.
Description of the drawings
Fig. 1 is that the oil moves the structural representation of displacement quadrotor unmanned plane to the utility model in one embodiment
Figure.
Fig. 2 is that the oil moves the first power rotation of displacement quadrotor unmanned plane to the utility model in one embodiment
The structure diagram of wing assembly.
Fig. 3 is that the oil moves the second power rotation of displacement quadrotor unmanned plane to the utility model in one embodiment
The structure diagram of wing assembly.
Fig. 4 is that the oil moves the vertical view of displacement quadrotor unmanned plane to the utility model in one embodiment.
Fig. 5 is that the oil moves the first power in displacement quadrotor unmanned plane and revolves the utility model in one embodiment
The cross-sectional view of the structure of wing assembly.
Wherein, the arrow in Fig. 4 represents direction of rotation, and the direction of rotation of the first power rotor assembly is reversion, and second is dynamic
The direction of rotation of power rotor assembly is rotates forward.
Specific embodiment
Below in conjunction with the accompanying drawings and embodiment is described in further detail the utility model, to enable people in the art
Member can implement according to this with reference to specification word.
It should be appreciated that such as " having ", "comprising" and " comprising " term used herein are not precluded one or more
The presence or addition of a other element or combinations.
As shown in fig. 1~fig. 5, the utility model provide in one embodiment a kind of dynamic displacement quadrotor of oil nobody
Machine, including：
Body 5, with cross-shaped supporting rod；
Power rotor system, including two the first power rotor assemblies 1 and two the second power rotor assemblies 2, with institute
The crosspoint of supporting rod is stated as symmetric points, described two first power rotor assemblies 1 symmetrically set up two in the supporting rod separately
End, described two second power rotor assemblies 2 symmetrically set up separately dynamic in remaining two ends of the supporting rod, described first
Power rotor assembly 1 and the second power rotor assembly 2 include the driving mechanism being fixed by the bracket on the supporting rod,
The transmission mechanism being sequentially connected with the driving mechanism and the pulp distance varying mechanism 11 being arranged on above the transmission mechanism and rotation
Wing mechanism 12, for fixing propeller, the pulp distance varying mechanism 11 is connect simultaneously the rotor mechanism 12 with the rotor mechanism 12
And for changing the rotation angle of attack of the propeller；The driving mechanism driving described first of the first power rotor assembly 1 is dynamic
The rotor mechanism 12 of power rotor assembly 1 carries out the rotation in a direction, the driving mechanism driving of the second power rotor assembly 2
The progress of rotor mechanism 12 of the second power rotor assembly 2 rotates in the opposite direction with a side；
Wherein, the driving mechanism of the first power rotor assembly 1 and the driving mechanism of the second power rotor assembly 2
It is aviation engine 6.
The transmission mechanism of the transmission mechanism of the first power rotor assembly 1 and the second power rotor assembly 2 wraps
Include the shaft coupling 7 being fixedly connected by screw with the aviation engine 6, be fixedly connected with the shaft coupling 7 it is unidirectional from
Clutch 8, the first order deceleration member being connected with the one-way clutch 8 by input shaft 20 and with the first order deceleration structure
The second level deceleration member of part rotation connection；
The first order deceleration member of transmission mechanism in the first power rotor assembly 1 slows down for three spur gear of the first order
Machine 9, the first order deceleration member of the transport mechanism in the second power rotor assembly 2 is two spur gear speed reducer of the first order
13, the second of the transmission mechanism in the first power rotor assembly 1 and the transport mechanism in the second power rotor assembly 2
Grade deceleration member is second level bevel gear reducing mechanism 10.
The pulp distance varying mechanism 11 include being fixed on steering engine 14 on the second level bevel gear reducing mechanism 10, lower end with
The first connecting rod 15 of the output terminal flexible connection of the steering engine 14, one end are flexibly connected and cover with the upper end of the first connecting rod 15
The displacement rocking bar 16 that is located at outside the output shaft 22 of the second level bevel gear reducing mechanism 10, upper end are lived with the displacement rocking bar 16
Displacement support arm 19 that dynamic connection and lower end are connect with the second level bevel gear reducing mechanism 10 is set in the second level and bores tooth
It takes turns the sliding shoe 17 connecting on the output shaft 22 of deceleration mechanism 10 and with the displacement rocking bar 16, be set in the second level cone tooth
Pushing block 18 and lower end on the output shaft 22 of wheel deceleration mechanism 10 and positioned at 17 top of sliding shoe connect with the pushing block 18
It connects and the upper paddle with the rotor mechanism 12 presss from both sides 24 second connecting rods 23 connecting, the first connecting rod 15 and the displacement support arm
19 respectively positioned at the both sides of the output shaft 22 of the second level bevel gear reducing mechanism 10.
Controller (not shown) is arranged on the body 5, and the controller is electrically connected with the aviation engine 6
It connects.
The three spur gear speed reducer 9 of the first order includes three the first spur gears, one of them first spur gear is used to change
To.
The two spur gear deceleration mechanism 13 of the first order includes two the second spur gears, one of them second spur gear is used for
Commutation.
The oil of the utility model moves the specific connection relation inside power rotor system in displacement quadrotor unmanned plane：
Power rotor system is divided into two kinds, is divided into two the first power rotor assemblies 1 (such as Fig. 2) and two the second power
Rotor assembly 2 (such as Fig. 3).
As shown in Fig. 2, the motion principle in two the first power rotor assemblies 1, in two the first power rotor assemblies 1
In, 7 one end of shaft coupling is connect by screw with aviation engine 6, the other end of shaft coupling 7 and one end of one-way clutch 8
Fixed, three spur gear deceleration mechanism 9 of the first order is connect, and the first order by input shaft 20 with the other end of one-way clutch 8
21 protruding three spur gear deceleration mechanism 9 of the first order of transition axis in three spur gear deceleration mechanisms 9 simultaneously extends to second level cone
It is connected thereto in tooth deceleration mechanism 10, so that carrying out second level cone tooth deceleration mechanism 10 carries out communtation deceleration, second level bevel gear
In hole of the output shaft 22 that deceleration mechanism 10 is stretched out by pitch-changing mechanism 11, rotor mechanism 12 is fixed on second level bevel gear and slows down
22 upper end of output shaft that mechanism 10 is stretched out, and be connected by second connecting rod 23 with pitch-changing mechanism 11, pulp distance varying mechanism 11 includes solid
Be scheduled on steering engine 14 on second level bevel gear reducing mechanism 10, one end steering engine 14 output terminal flexible connection first connecting rod 15,
One end is flexibly connected with the other end of first connecting rod 15 and is set in outside the output shaft 22 of second level bevel gear reducing mechanism 10
Displacement rocking bar 16, the displacement that one end is flexibly connected with displacement rocking bar 16 and the other end is connect with second level bevel gear reducing mechanism 10
Support arm 19, the sliding shoe 17 for being set on the output shaft 22 of second level bevel gear reducing mechanism 10 and being connect with displacement rocking bar 16,
The pushing block 18 and one for being set on the output shaft 22 of second level bevel gear reducing mechanism 10 and being connect with the upper end of sliding shoe 17
The second connecting rod 23 that end is connect with pushing block 18 and the other end is connect with the paddle folder 24 in rotor mechanism 12；
Wherein, steering engine 14 is rotated by the way that first connecting rod 15 is driven to move up and down, so as to which displacement rocking bar 16 be driven to drive
Sliding shoe 17 is slided up and down along the output shaft 22 of second level bevel gear reducing mechanism 10, and sliding shoe 17 drives pushing block 18 along the
The output shaft 22 of two level bevel gear reducing mechanism 10 slides up and down, and pushing block 18 drives second connecting rod 23 transport up and down again
Dynamic, second connecting rod 23 drives paddle folder 24 to be rotated, and then drives rotor mechanism 12, to change the rotation angle of attack of propeller, comes
Realize that this oil moves the actions such as the lifting pitching rolling of displacement quadrotor unmanned plane.
As shown in figure 3, the motion principle of two the second power rotor assemblies 2, two in two the second power rotor assemblies 2
Three spur gear deceleration mechanism 9 of the first order is changed to two spur gear of the first order on the basis of in a first power rotor assembly 1 to subtract
Fast mechanism 13, other are identical with two the first power rotor assemblies 1.
The operation principle of the utility model：
The aviation that the oil of the utility model is moved in displacement quadrotor unmanned plane is defeated by controller control igniting with engine 6
Go out constant rotational speed, shaft coupling 7 is driven to be separately input to three spur gear deceleration mechanism 9 and first of the first order by one-way clutch 8
Two spur gear deceleration mechanisms 13 of grade slow down, wherein the three spur gear deceleration mechanism 9 of the first order in the first power rotor assembly 1
For three the first spur gears, the two spur gear deceleration mechanism 13 of the first order in the second power rotor assembly 2 is two the second straight-tooth
Wheel, one of them first spur gear and one of them second spur gear are used to commutate, three spur gear deceleration mechanism of the first order, 9 He
The rotating speed direction of rotation of two spur gear deceleration mechanism 13 of first order output is different, after power be input to second level bevel gear slow down
In mechanism 10, then passing on rotor mechanism 12, the rotor mechanism 12 being respectively formed in two the first power rotor assemblies 1 inverts,
Rotor mechanism 12 in two the second power rotor assemblies 2 rotates forward, thus when the utility model oil move displacement quadrotor nobody
When machine is balanced flight, gyroscopic effect and air force torque effect are cancelled completely.
The oil of the utility model moves power transmission in displacement quadrotor unmanned plane by the way of axis transmission, is not in
Because of synchronous belt tension, the power loss for avoiding causing unmanned plane is larger；And in flame-out landing, synchronous belt mistake will not occur
It the phenomenon that pine and easily skidding, avoids damaging unmanned plane.
Although the embodiment of the utility model is disclosed as above, it is not restricted in specification and embodiment
Listed utilization, it can be applied to various fields suitable for the present invention completely, for those skilled in the art,
Other modification is easily implemented, therefore without departing from the general concept defined in the claims and the equivalent scope, this reality
Specific details and legend shown and described herein are not limited to novel.
Claims (6)
1. a kind of dynamic displacement quadrotor unmanned plane of oil, which is characterized in that including：
Body, with cross-shaped supporting rod；
Power rotor system, including two the first power rotor assemblies and two the second power rotor assemblies, with the support
The crosspoint of bar is symmetric points, and described two first power rotor assemblies symmetrically set up separately in two ends of the supporting rod, institute
It states two the second power rotor assemblies symmetrically to set up separately in remaining two ends of the supporting rod, the first power rotor is total
Into the driving mechanism and the driving for including being fixed by the bracket on the supporting rod with the second power rotor assembly
The transmission mechanism of mechanism driving connection and the pulp distance varying mechanism and rotor mechanism being arranged on above the transmission mechanism, the rotation
For fixing propeller, the pulp distance varying mechanism with the rotor mechanism connect and for changing the propeller wing mechanism
Rotate the angle of attack；The driving mechanism of the first power rotor assembly drives the rotor mechanism of the first power rotor assembly to carry out
The rotation in one direction, the driving mechanism of the second power rotor assembly drive the gyroplane of the second power rotor assembly
Structure progress rotates in the opposite direction with a side；
Wherein, the driving mechanism of the first power rotor assembly and the driving mechanism of the second power rotor assembly are boat
Sky engine.
A kind of 2. dynamic displacement quadrotor unmanned plane of oil according to claim 1, which is characterized in that the first power rotor
The transmission mechanism of the transmission mechanism of assembly and the second power rotor assembly is included through screw and the aviation with starting
Shaft coupling that machine is fixedly connected, the one-way clutch being fixedly connected with the shaft coupling, by input shaft and the one-way clutch
The first order deceleration member that device is connected and the second level deceleration member with first order deceleration member rotation connection；
The first order deceleration member of transmission mechanism in the first power rotor assembly be three spur gear speed reducer of the first order, institute
The first order deceleration member of the transport mechanism in the second power rotor assembly is stated as two spur gear speed reducer of the first order, described first
Transmission mechanism in power rotor assembly and the second level deceleration member of the transport mechanism in the second power rotor assembly are equal
For second level bevel gear reducing mechanism.
A kind of 3. dynamic displacement quadrotor unmanned plane of oil according to claim 2, which is characterized in that the pulp distance varying mechanism packet
Include the steering engine being fixed on the second level bevel gear reducing mechanism, first that lower end is flexibly connected with the output terminal of the steering engine
Connecting rod, one end are flexibly connected with the upper end of the first connecting rod and are set in the output shaft of the second level bevel gear reducing mechanism
Outer displacement rocking bar, upper end are flexibly connected with the displacement rocking bar and lower end is connect with the second level bevel gear reducing mechanism
Displacement support arm, the slip for being set on the output shaft of the second level bevel gear reducing mechanism and being connect with the displacement rocking bar
Block, the pushing block for being set on the output shaft of the second level bevel gear reducing mechanism and being located above the sliding shoe and lower end
It is connect with the pushing block and upper end presss from both sides the second connecting rod connected, the first connecting rod and the change with the paddle in the rotor mechanism
Away from support arm respectively positioned at the both sides of the output shaft of the second level bevel gear reducing mechanism.
4. the dynamic displacement quadrotor unmanned plane of a kind of oil according to claim 1, which is characterized in that further include：
Controller is arranged on the body, and the controller and the aviation are with starting mechatronics.
A kind of 5. dynamic displacement quadrotor unmanned plane of oil according to claim 2, which is characterized in that three straight-tooth of the first order
It takes turns speed reducer and includes three the first spur gears, one of them first spur gear is used to commutate.
A kind of 6. dynamic displacement quadrotor unmanned plane of oil according to claim 2, which is characterized in that two straight-tooth of the first order
It takes turns deceleration mechanism and includes two the second spur gears, one of them second spur gear is used to commutate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721551492.9U CN207466966U (en) | 2017-11-17 | 2017-11-17 | A kind of dynamic displacement quadrotor unmanned plane of oil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721551492.9U CN207466966U (en) | 2017-11-17 | 2017-11-17 | A kind of dynamic displacement quadrotor unmanned plane of oil |
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| Publication Number | Publication Date |
|---|---|
| CN207466966U true CN207466966U (en) | 2018-06-08 |
Family
ID=62261394
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721551492.9U Active CN207466966U (en) | 2017-11-17 | 2017-11-17 | A kind of dynamic displacement quadrotor unmanned plane of oil |
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| CN (1) | CN207466966U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107757904A (en) * | 2017-11-17 | 2018-03-06 | 北京航景创新科技有限公司 | A kind of dynamic rotor wing unmanned aerial vehicle of displacement four of oil |
| CN109083431A (en) * | 2018-08-24 | 2018-12-25 | 南昌理工学院 | Glass cleaning system based on unmanned plane |
| CN110341939A (en) * | 2019-08-30 | 2019-10-18 | 吉林大学 | A kind of H-type variablepiston quadrotor plant protection drone |
-
2017
- 2017-11-17 CN CN201721551492.9U patent/CN207466966U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107757904A (en) * | 2017-11-17 | 2018-03-06 | 北京航景创新科技有限公司 | A kind of dynamic rotor wing unmanned aerial vehicle of displacement four of oil |
| CN109083431A (en) * | 2018-08-24 | 2018-12-25 | 南昌理工学院 | Glass cleaning system based on unmanned plane |
| CN110341939A (en) * | 2019-08-30 | 2019-10-18 | 吉林大学 | A kind of H-type variablepiston quadrotor plant protection drone |
| CN110341939B (en) * | 2019-08-30 | 2022-08-16 | 吉林大学 | Four rotor plant protection unmanned aerial vehicle of H type feather |
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Legal Events
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: An oil powered variable pitch quadrotor UAV Effective date of registration: 20200820 Granted publication date: 20180608 Pledgee: Beijing Yanhong Financing Guarantee Co.,Ltd. Pledgor: BEIJING HANGJING INNOVATION SCIENCE & TECHNOLOGY Co.,Ltd. Registration number: Y2020990001003 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20210824 Granted publication date: 20180608 Pledgee: Beijing Yanhong Financing Guarantee Co.,Ltd. Pledgor: BEIJING HANGJING INNOVATION SCIENCE & TECHNOLOGY Co.,Ltd. Registration number: Y2020990001003 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: An oil powered variable pitch four rotor UAV Effective date of registration: 20210924 Granted publication date: 20180608 Pledgee: Beijing Yanhong Financing Guarantee Co.,Ltd. Pledgor: BEIJING HANGJING INNOVATION SCIENCE & TECHNOLOGY Co.,Ltd. Registration number: Y2021990000876 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20230105 Granted publication date: 20180608 Pledgee: Beijing Yanhong Financing Guarantee Co.,Ltd. Pledgor: BEIJING HANGJING INNOVATION SCIENCE & TECHNOLOGY CO.,LTD. Registration number: Y2021990000876 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A Hydrodynamic Variable Pitch Four-rotor UAV Effective date of registration: 20230214 Granted publication date: 20180608 Pledgee: Beijing Yanhong Financing Guarantee Co.,Ltd. Pledgor: BEIJING HANGJING INNOVATION SCIENCE & TECHNOLOGY CO.,LTD. Registration number: Y2023110000065 |