CN109383777A - A kind of unmanned plane body - Google Patents
A kind of unmanned plane body Download PDFInfo
- Publication number
- CN109383777A CN109383777A CN201710657259.7A CN201710657259A CN109383777A CN 109383777 A CN109383777 A CN 109383777A CN 201710657259 A CN201710657259 A CN 201710657259A CN 109383777 A CN109383777 A CN 109383777A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- axis
- landing
- balance
- unmanned plane
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000009434 installation Methods 0.000 claims abstract description 18
- 230000005484 gravity Effects 0.000 claims abstract description 11
- 238000004891 communication Methods 0.000 claims abstract description 4
- RKTYLMNFRDHKIL-UHFFFAOYSA-N copper;5,10,15,20-tetraphenylporphyrin-22,24-diide Chemical compound [Cu+2].C1=CC(C(=C2C=CC([N-]2)=C(C=2C=CC=CC=2)C=2C=CC(N=2)=C(C=2C=CC=CC=2)C2=CC=C3[N-]2)C=2C=CC=CC=2)=NC1=C3C1=CC=CC=C1 RKTYLMNFRDHKIL-UHFFFAOYSA-N 0.000 claims description 4
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 3
- 230000003044 adaptive effect Effects 0.000 claims description 3
- 230000001133 acceleration Effects 0.000 claims 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 claims 1
- 239000010931 gold Substances 0.000 claims 1
- 229910052737 gold Inorganic materials 0.000 claims 1
- 230000037396 body weight Effects 0.000 abstract description 4
- 230000001939 inductive effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 3
- 230000000087 stabilizing effect Effects 0.000 description 3
- 239000003292 glue Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 239000000084 colloidal system Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
- B64D45/06—Landing aids; Safety measures to prevent collision with earth's surface mechanical
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of unmanned plane bodies, including fuselage, two side axles, tailing axle, detachable carry axis and landing balance system, the front of fuselage is equipped with ultrasonic distance measuring module installing port, the top of fuselage is equipped with telecontrol antenna, tail the tip of the axis is equipped with communication antenna, installation part is equipped in two side axles, tailing axle is equipped with connector, driving motor and multiple fixing pieces are equipped on installation part and connector, driving motor is equipped with multiple rotors, balance system of landing includes landing stable equilibrium's axis and arc balance element, gravity sensing device and balance control device are equipped in fuselage, gravity sensing device is used for inductive drop stable equilibrium shaft balancing state, balance control device is in a vertical state for controlling landing stable equilibrium's axis.The present invention solves the problems, such as that cylinder block strength is low in the prior art, body weight is big, fuselage is difficult to balance, at high cost and installation is inconvenient, passes through landing stable equilibrium's axis and arc balance element guarantees the balance of unmanned plane.
Description
Technical field
The present invention relates to a kind of unmanned plane bodies, belong to air vehicle technique field.
Background technique
Unmanned plane is using the not manned aircraft of radio robot and the presetting apparatus provided for oneself manipulation, extensively
Be applied to dual-use field, unmanned plane it is many kinds of, mainly include fixed-wing unmanned plane, flapping wing unmanned plane and more rotation
Wing unmanned plane etc., due to manipulating simple, high reliablity, and do not need runway can VTOL, can be in sky after taking off
Middle hovering, therefore relative to fixed-wing unmanned plane and flapping wing unmanned plane, multi-rotor unmanned aerial vehicle has obtained extensively in every field
Using.
Multi-rotor unmanned aerial vehicle, generally include the body positioned at unmanned plane center, multiple horns for being connect with body with
And be set to the motor and rotor of each horn end, in the prior art, body is integrally in class cuboid, generally by upper cover, under
Bottom and the side plate three parts composition for being surrounded by body side, wherein mounting hole is opened up on side plate, by the way that horn is inserted into the installation
In hole, and using the connection of gluing realization horn and body between hole inner wall and horn periphery.
It for unmanned plane, on the one hand needs fuselage weight light as far as possible, on the other hand needs to guarantee that body is strong again
Degree, it is also necessary to be able to maintain balance, it is big that the body of above-mentioned class cuboid is from air power in flight course, in order to enhance machine
The intensity of body, it usually needs body is made using the metal material with certain degree of hardness, or is needed using the light of higher cost
Matter strong hardness material is difficult to mitigate fuselage weight simultaneously and reduces fuselage cost, thus, the body of above structure and shape exists
Mitigate fuselage weight and drop low cost aspect, has become the bottleneck of technology.
In addition, open up the mode of mounting hole connection horn on side plate, on the one hand due to aperture and horn difference in diameter compared with
Small, when horn is inserted into mounting hole, operation precision is required high, and needs that fuselage is put into glue before structure glue is uncured
It closes and is positioned in tooling, be not easy to the installation of horn, on the other hand when the colloid between hole inner wall and horn periphery is arranged not
Sealing is not achieved when uniform, between horn and mounting hole wall, in harsh environment when flight, is easily damaged machine intracorporal zero
Part, the above-mentioned technical problems in the prior art, currently no effective solution has been proposed.
Summary of the invention
The main object of the present invention is to provide for a kind of unmanned plane body, with solve in the prior art cylinder block strength it is low,
Body weight is big, fuselage is difficult to the problem balanced, at high cost and installation is inconvenient.
The purpose of the present invention can reach by using following technical solution:
A kind of unmanned plane body, including fuselage, two side axles, tailing axle, detachable carry axis and landing balance system, the drop
The two sides that two side axles are arranged in balance system are fallen, the two sides of the fuselage, the tail is symmetrically arranged in two side axles
The rear of the fuselage is arranged in axis, and the lower section of the fuselage, the front of the fuselage is arranged in the detachable carry axis
Equipped with ultrasonic distance measuring module installing port, the top of the fuselage is equipped with telecontrol antenna, and the tail the tip of the axis is equipped with communication day
Line is equipped with installation part in two side axles, and the installation part is equipped with image capture module installing port, and the tailing axle is equipped with
Driving motor and multiple fixing pieces are equipped on connector, the installation part and the connector, the driving motor is equipped with
Multiple rotors, the rotor are equipped with rotor stabilizing member, and the fuselage is equipped with multiple radiators, the detachable carry axis
Lower section is equipped with control motor, and the landing balance system includes landing stable equilibrium's axis and arc balance element, the arc balance
Slide slot is equipped in part, landing stable equilibrium's axis is arranged in the slide slot, and gravity sensing is equipped in the fuselage and is filled
It sets and balance control device, the gravity sensing device is described flat for incuding the landing stable equilibrium shaft balancing state
Weighing apparatus control device is in a vertical state for controlling landing stable equilibrium's axis, and the fuselage is made to keep equilibrium state.
Further, inner loop control unit and outer loop-control unit are equipped in the balance control device；The inner ring control
Unit processed is used to control the posture of landing stable equilibrium's axis and the arc balance element；The outer loop-control unit is for controlling
Make the angle of position and the arc balance element of the landing stable equilibrium's axis in the arc balance element.
Further, the inner loop control unit uses adaptive robust control algorithm and mahony algorithm, the outer ring
Control unit uses Fuzzy PID.
Further, the mahony algorithm is the data according to accelerometer and magnetometer, is transformed into geographic coordinate system
Afterwards, it carries out seeking error with the gravity vector of corresponding reference and ground magnetic vector, this error is used to correct the output of gyroscope, then
Quaternary number update, reconvert to Eulerian angles are carried out with gyro data.
Further, the fuselage is tetragonal fuselage, and four angles of the quadrangle fuselage connect equipped with intelligent charge
Mouthful.
Further, four angles of the tetragonal fuselage are equipped with memory, and the memory is for storing unmanned plane
Instruction and flight control system data, are also used to store position, speed and the posture of unmanned plane.
Further, landing stable equilibrium's axis is metal shaft, and the end of landing stable equilibrium's axis is equipped with power-assist
Sliding structure, the power-assist sliding structure smoothly slide in the slide slot for the landing stable equilibrium axis.
Further, the end of landing stable equilibrium's axis and the junction of the slide slot are equipped with and slide locked knot
Structure, the locking structure that slides prevent described for being locked after fuselage balance to landing stable equilibrium's axis
Landing stable equilibrium's axis breaks away.
Further, the outside of the arc balance element is equipped with yielding rubber layer, and the yielding rubber layer is used at nobody
When machine lands, vibration is reduced.
Advantageous effects of the invention: unmanned plane body according to the invention, unmanned plane body provided by the invention, solution
Cylinder block strength in the prior art of having determined is low, body weight is big, fuselage is difficult to the problem balanced, at high cost and installation is inconvenient, passes through
Landing stable equilibrium's axis and arc balance element can be good at guaranteeing the balance of unmanned plane.
Detailed description of the invention
Fig. 1 is the stereoscopic schematic diagram of a preferred embodiment of unmanned plane body according to the invention.
In figure: 11- ultrasonic distance measuring module installing port, 12- image capture module installing port, 14- intelligent charge interface,
17- radiator, 19- telecontrol antenna, 20- fuselage, 21- side axle, 22- tailing axle, 23- installation part, 24- connector, 25- driving electricity
Machine, 26- rotor stabilizing member, 27- rotor, 28- fixing piece, the detachable carry axis of 29-, 30- control motor, and 31- landing is stablized flat
Weigh axis, 32- arc balance element, 33- slide slot.
Specific embodiment
To make the more clear and clear technical solution of the present invention of those skilled in the art, below with reference to examples and drawings
The present invention is described in further detail, and embodiments of the present invention are not limited thereto.
As shown in Figure 1, a kind of unmanned plane body provided in this embodiment, including fuselage 20, two side axles 21, tailing axle 22, can
Carry axis 29 and landing balance system are dismantled, the two sides of two side axles 21, two sides are arranged in the landing balance system
The two sides of the fuselage 20 are symmetrically arranged in axis 21, and the rear of the fuselage 20 is arranged in the tailing axle 22, described detachable
The lower section of the fuselage 20 is arranged in carry axis 29, and the front of the fuselage 20 is equipped with ultrasonic distance measuring module installing port 11,
The top of the fuselage 20 is equipped with telecontrol antenna 19, and the end of the tailing axle 22 is equipped with communication antenna, in two side axles 21
Equipped with installation part 23, the installation part 23 is equipped with image capture module installing port 12, and the tailing axle 22 is equipped with connector 24,
It is equipped with driving motor 25 and multiple fixing pieces 28 on the installation part 23 and the connector 24, is set on the driving motor 25
Have multiple rotors 27, the rotor 27 is equipped with rotor stabilizing member 26, and the fuselage 20 is equipped with multiple radiators 17, it is described can
The lower section for dismantling carry axis 29 is equipped with control motor 30, and the landing balance system includes that landing stable equilibrium's axis 31 and arc are flat
Weigh part 32, and slide slot 33 is equipped in the arc balance element 32, and the landing stable equilibrium axis 31 is arranged in the slide slot 33
It is interior, gravity sensing device and balance control device are equipped in the fuselage 20, the gravity sensing device is for incuding the drop
The equilibrium state of stable equilibrium's axis 31 is fallen, the balance control device is in vertical for controlling the landing stable equilibrium axis 31
State makes the fuselage 20 keep equilibrium state.
Further, in the present embodiment, inner loop control unit and outer loop control list are equipped in the balance control device
Member；The inner loop control unit is used to control the posture of landing stable equilibrium's axis 31 and the arc balance element 32；It is described
Outer loop-control unit is used to control position and the arc of the landing stable equilibrium's axis 31 in the arc balance element 32
The angle of balance element 32；The inner loop control unit uses adaptive robust control algorithm and mahony algorithm, the outer ring control
Unit processed uses Fuzzy PID；The mahony algorithm is the data according to accelerometer and magnetometer, is transformed into ground
It after managing coordinate system, carries out seeking error with the gravity vector of corresponding reference and ground magnetic vector, this error is used to correct gyroscope
Output, then carries out quaternary number update, reconvert to Eulerian angles with gyro data.
Further, in the present embodiment, as shown in Figure 1, the fuselage 20 is tetragonal fuselage, the quadrangle fuselage
Four angles be equipped with intelligent charge interface 14；Four angles of the quadrangle fuselage are equipped with memory, and the memory is used
In the instruction of storage unmanned plane and flight control system data, it is also used to store position, speed and the posture of unmanned plane.
Further, in the present embodiment, as shown in Figure 1, the landing stable equilibrium axis 31 is metal shaft, the landing
The end of stable equilibrium's axis 31 is equipped with power-assist sliding structure, and the power-assist sliding structure exists for the landing stable equilibrium axis 31
It is smoothly slided in the slide slot 33；The end of landing stable equilibrium's axis 31 and the junction of the slide slot 33 are equipped with and slide
Row locking structure, the locking structure that slides is for carrying out the landing stable equilibrium axis 31 after the fuselage 20 balance
It is locked, prevent the landing stable equilibrium axis 31 from breakking away；The outside of the arc balance element 32 is equipped with yielding rubber layer, institute
Yielding rubber layer is stated for reducing vibration in unmanned plane landing.
In conclusion in the present embodiment, according to the unmanned plane body of the present embodiment, unmanned plane machine provided in this embodiment
Body solves the problems, such as that cylinder block strength is low in the prior art, body weight is big, fuselage is difficult to balance, at high cost and installation is inconvenient,
It can be good at guaranteeing the balance of unmanned plane by landing stable equilibrium's axis and arc balance element.
The above, further embodiment only of the present invention, but scope of protection of the present invention is not limited thereto, and it is any
Within the scope of the present disclosure, according to the technique and scheme of the present invention and its design adds those familiar with the art
With equivalent substitution or change, protection scope of the present invention is belonged to.
Claims (9)
1. a kind of unmanned plane body, it is characterised in that: including fuselage (20), two side axles (21), tailing axle (22), detachable carry axis
(29) it is arranged with landing balance system, the landing balance system in the two sides of two side axles (21), two side axles (21)
In the two sides of the fuselage (20), tailing axle (22) setting is described removable at the rear of the fuselage (20) for symmetrical setting
Carry axis (29) setting is unloaded in the lower section of the fuselage (20), the front of the fuselage (20) is pacified equipped with ultrasonic distance measuring module
It filling mouth (11), the top of the fuselage (20) is equipped with telecontrol antenna (19), and the end of the tailing axle (22) is equipped with communication antenna, and two
It is equipped with installation part (23) on the side axle (21), the installation part (23) is equipped with image capture module installing port (12), institute
It states tailing axle (22) and is equipped with connector (24), be equipped with driving motor (25) on the installation part (23) and the connector (24)
With multiple fixing pieces (28), the driving motor (25) is equipped with multiple rotors (27), and it is steady that the rotor (27) is equipped with rotor
Determine part (26), the fuselage (20) is equipped with multiple radiators (17), and the lower section of the detachable carry axis (29) is equipped with control
Motor (30), the landing balance system include landing stable equilibrium's axis (31) and arc balance element (32), the arc balance
Slide slot (33) are equipped in part (32), landing stable equilibrium axis (31) setting is in the slide slot (33), the fuselage
(20) gravity sensing device and balance control device are equipped in, the gravity sensing device is for incuding the landing stable equilibrium
The equilibrium state of axis (31), the balance control device is in a vertical state for controlling the landing stable equilibrium axis (31),
The fuselage (20) are made to keep equilibrium state.
2. a kind of unmanned plane body according to claim 1, it is characterised in that: be equipped with inner ring in the balance control device
Control unit and outer loop-control unit；The inner loop control unit is for controlling the landing stable equilibrium axis (31) and the arc
The posture of shape balance element (32)；The outer loop-control unit is flat in the arc for controlling the landing stable equilibrium axis (31)
Weigh the position in part (32) and the angle of the arc balance element (32).
3. a kind of unmanned plane body according to claim 2, it is characterised in that: the inner loop control unit is using adaptive
Robust Control Algorithm and mahony algorithm, the outer loop-control unit use Fuzzy PID.
4. a kind of unmanned plane body according to claim 3, it is characterised in that: the mahony algorithm is according to acceleration
The data of meter and magnetometer after being transformed into geographic coordinate system, carry out seeking error with the gravity vector of corresponding reference and ground magnetic vector,
This error is used to correct the output of gyroscope, then carries out quaternary number update, reconvert to Eulerian angles with gyro data.
5. a kind of unmanned plane body according to claim 1, it is characterised in that: the fuselage (20) is tetragonal fuselage,
Four angles of the quadrangle fuselage are equipped with intelligent charge interface (14).
6. a kind of unmanned plane body according to claim 5, it is characterised in that: set on four angles of the quadrangle fuselage
There is memory, the memory is also used to store the position of unmanned plane for storing unmanned plane instruction and flight control system data
It sets, speed and posture.
7. a kind of unmanned plane body according to claim 1, it is characterised in that: the landing stable equilibrium axis (31) is gold
Belong to axis, the end of landing stable equilibrium's axis (31) is equipped with power-assist sliding structure, and the power-assist sliding structure is used for the drop
Stable equilibrium's axis (31) is fallen smoothly to slide in the slide slot (33).
8. a kind of unmanned plane body according to claim 7, it is characterised in that: the end of landing stable equilibrium's axis (31)
The junction of head and the slide slot (33), which is equipped with, slides locking structure, and the locking structure that slides is in the fuselage (20)
After balance, the landing stable equilibrium axis (31) is locked, prevents the landing stable equilibrium axis (31) from breakking away.
9. a kind of unmanned plane body according to claim 1, it is characterised in that: set on the outside of the arc balance element (32)
There is yielding rubber layer, the yielding rubber layer is used to reduce vibration in unmanned plane landing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710657259.7A CN109383777B (en) | 2017-08-03 | 2017-08-03 | Unmanned aerial vehicle organism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710657259.7A CN109383777B (en) | 2017-08-03 | 2017-08-03 | Unmanned aerial vehicle organism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109383777A true CN109383777A (en) | 2019-02-26 |
| CN109383777B CN109383777B (en) | 2020-08-21 |
Family
ID=65413075
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710657259.7A Active CN109383777B (en) | 2017-08-03 | 2017-08-03 | Unmanned aerial vehicle organism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109383777B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114415505A (en) * | 2021-12-30 | 2022-04-29 | 天津理工大学 | Tail wing self-adaptive anti-interference control method of flapping wing robot |
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|---|---|---|---|---|
| CN104943858A (en) * | 2015-07-03 | 2015-09-30 | 广西大学 | Multifunctional coaxial double-rotor-wing four-shaft aircraft |
| CN205602093U (en) * | 2016-04-01 | 2016-09-28 | 郑州郑航通用航空工业科技有限公司 | Unmanned plant protection machine undercarriage |
| CN205916325U (en) * | 2016-07-04 | 2017-02-01 | 燕山大学里仁学院 | Automatic unmanned aerial vehicle who patrols line of electric wire netting |
| CN206012957U (en) * | 2016-08-30 | 2017-03-15 | 华斌 | A kind of Multi-axis aircraft |
| CN106741881A (en) * | 2016-12-27 | 2017-05-31 | 天津寰宇地理信息有限公司 | A kind of agricultural machinery unmanned plane undercarriage |
| CN106828889A (en) * | 2017-01-19 | 2017-06-13 | 福州大学 | Unmanned plane protection device and its method of work |
-
2017
- 2017-08-03 CN CN201710657259.7A patent/CN109383777B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104943858A (en) * | 2015-07-03 | 2015-09-30 | 广西大学 | Multifunctional coaxial double-rotor-wing four-shaft aircraft |
| CN205602093U (en) * | 2016-04-01 | 2016-09-28 | 郑州郑航通用航空工业科技有限公司 | Unmanned plant protection machine undercarriage |
| CN205916325U (en) * | 2016-07-04 | 2017-02-01 | 燕山大学里仁学院 | Automatic unmanned aerial vehicle who patrols line of electric wire netting |
| CN206012957U (en) * | 2016-08-30 | 2017-03-15 | 华斌 | A kind of Multi-axis aircraft |
| CN106741881A (en) * | 2016-12-27 | 2017-05-31 | 天津寰宇地理信息有限公司 | A kind of agricultural machinery unmanned plane undercarriage |
| CN106828889A (en) * | 2017-01-19 | 2017-06-13 | 福州大学 | Unmanned plane protection device and its method of work |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114415505A (en) * | 2021-12-30 | 2022-04-29 | 天津理工大学 | Tail wing self-adaptive anti-interference control method of flapping wing robot |
| CN114415505B (en) * | 2021-12-30 | 2023-08-15 | 天津理工大学 | Tail wing self-adaptive anti-interference control method of flapping wing robot |
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| Publication number | Publication date |
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| CN109383777B (en) | 2020-08-21 |
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Address after: 100000 Beijing Road, Haidian District, Lane No. 1, building 5, floor 5-1614, 1 Applicant after: CCCC remote sensing load (Jiangsu) Technology Co.,Ltd. Address before: 100000 Beijing Road, Haidian District, Lane No. 1, building 5, floor 5-1614, 1 Applicant before: ZHONGJIAO REMOTE SENSING LOAD (BEIJING) TECHNOLOGY Co.,Ltd. |
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Effective date of registration: 20200701 Address after: 214000 Jiangsu Wuxi City Gu Valley Business Park 37-203 Applicant after: CHINA COMMUNICATIONS REMOTE SENSING TIANYU TECHNOLOGY JIANGSU Co.,Ltd. Address before: 100000 Beijing Road, Haidian District, Lane No. 1, building 5, floor 5-1614, 1 Applicant before: CCCC remote sensing load (Jiangsu) Technology Co.,Ltd. |
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Denomination of invention: A kind of UAV body Effective date of registration: 20210122 Granted publication date: 20200821 Pledgee: Wuxi Branch of Bank of Beijing Co.,Ltd. Pledgor: CHINA COMMUNICATIONS REMOTE SENSING TIANYU TECHNOLOGY JIANGSU Co.,Ltd. Registration number: Y2021320010028 |