CN116161238A - Multi-rotor aircraft broken-blade detection device - Google Patents
Multi-rotor aircraft broken-blade detection device Download PDFInfo
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- CN116161238A CN116161238A CN202310176486.3A CN202310176486A CN116161238A CN 116161238 A CN116161238 A CN 116161238A CN 202310176486 A CN202310176486 A CN 202310176486A CN 116161238 A CN116161238 A CN 116161238A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D5/00—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable
- G01D5/48—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using wave or particle radiation means
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06K—GRAPHICAL DATA READING; PRESENTATION OF DATA; RECORD CARRIERS; HANDLING RECORD CARRIERS
- G06K19/00—Record carriers for use with machines and with at least a part designed to carry digital markings
- G06K19/06—Record carriers for use with machines and with at least a part designed to carry digital markings characterised by the kind of the digital marking, e.g. shape, nature, code
- G06K19/067—Record carriers with conductive marks, printed circuits or semiconductor circuit elements, e.g. credit or identity cards also with resonating or responding marks without active components
- G06K19/07—Record carriers with conductive marks, printed circuits or semiconductor circuit elements, e.g. credit or identity cards also with resonating or responding marks without active components with integrated circuit chips
- G06K19/0722—Record carriers with conductive marks, printed circuits or semiconductor circuit elements, e.g. credit or identity cards also with resonating or responding marks without active components with integrated circuit chips comprising an arrangement for testing the record carrier
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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computer Hardware Design (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Theoretical Computer Science (AREA)
- Testing Of Short-Circuits, Discontinuities, Leakage, Or Incorrect Line Connections (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
Abstract
The invention discloses a multi-rotor aircraft pitch-breaking detection device, which comprises an electronic tag arranged in a blade and a reader-writer arranged on a horn, wherein the electronic tag comprises a read-write coil and a detection conductor, the detection conductor is arranged from the blade root to the blade tip, two ends of the detection conductor are electrically connected with the read-write coil, the read-write coil and the detection conductor form a circuit loop, the detection conductor is arranged from the blade root to the blade tip along the blade, and the detection conductor and the read-write coil are connected in series to form the circuit loop.
Description
Technical Field
The invention relates to the technical field of aircraft flight safety, in particular to a multi-rotor aircraft broken-blade detection device.
Background
In the flight process of the multi-rotor aircraft, the phenomenon of broken paddles caused by bird impact or fatigue of the paddles is unavoidable, and the dynamic balance of the paddles is definitely seriously destroyed, and huge vibration is generated, so that the flight safety of the aircraft is greatly negatively influenced. At present, the corresponding rotor motors need to be manually closed after the rotor is broken to avoid secondary injury to the aircraft and passengers, which is quite dependent on the experience and response speed of the pilot (the phenomenon of breaking the rotor of the multi-rotor aircraft is found).
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide a multi-rotor aircraft broken-blade detection device so as to solve the problem that the existing multi-rotor aircraft lacks monitoring of broken-blade phenomenon.
The invention adopts the following technical scheme:
the utility model provides a disconnected oar detection device of many rotor crafts for detect the state of the epaxial paddle of drive of horn, including locating electronic tags in the paddle and locate the reader-writer of horn, electronic tags includes read-write coil and detects the conductor, detect the conductor along the oar root of paddle is arranged to the oar point, just detect the both ends electricity of conductor connect in read-write coil, read-write coil and detect the conductor and constitute a circuit loop.
In certain alternative embodiments, the detection conductor extends through the leading and trailing edges of the blade.
In certain alternative embodiments, the electronic tag further comprises a memory unit, the read-write coil, and the detection conductor being connected in series.
In some optional embodiments, the number of paddles on each driving shaft is multiple, paddle roots of multiple paddles are connected through a connecting component, the read-write coil is arranged in the connecting component, and the read-write coil is located on the rotation axis of the paddles.
In some optional embodiments, the number of paddles on each driving shaft is provided with a plurality, and one of the paddles is provided with the read-write coil, the paddles of the plurality of paddles are connected through a connecting component, the detection conductor in the paddle without the read-write coil passes through the connecting component and is connected to the read-write coil, and the detection conductor in the plurality of paddles is connected in series with the read-write coil.
In certain alternative embodiments, the read-write coil is located at the paddle root of the paddle.
In some alternative embodiments, the electronic tag includes a flexible printed board, the paddle has a receiving cavity therein, the flexible printed board is disposed in the receiving cavity, and the sensing conductor is disposed in the flexible printed board.
In some optional embodiments, a thrust surface of a blade root of the blade is provided with a groove, and two ends of the detection conductor are exposed to inner side walls of the groove; the mounting seat is detachably arranged in the groove, the read-write coil is arranged in the mounting seat, and the input end and the output end of the read-write coil are exposed to the outer side wall of the mounting seat; the input end and the output end of the read-write coil are respectively abutted to the two ends of the detection conductor.
In some alternative embodiments, the connecting member is provided with a groove, and both ends of the detecting conductor are exposed to the inner side wall of the groove; the mounting seat is detachably arranged in the groove, the read-write coil is arranged in the mounting seat, and the input end and the output end of the read-write coil are exposed to the outer side wall of the mounting seat; the input end and the output end of the read-write coil are respectively abutted to the two ends of the detection conductor.
In order to solve the same technical problems, the invention also provides an aircraft, which comprises the multi-rotor aircraft pitch-breaking detection device.
Compared with the prior art, the invention has the beneficial effects that:
the detection conductor is arranged along the blade root to the blade tip of the blade, and because the detection conductor and the reading coil are connected in series to form a circuit loop, when the blade breaks, the detection conductor can be disconnected along with the breaking of the blade, so that the circuit loop is broken, and a reader-writer on the horn can not read information through the reading coil, so that the occurrence of the phenomenon of breaking the blade can be judged.
Drawings
FIG. 1 is a schematic structural view of an inventive multi-rotor aircraft pitch detection device;
in the figure: 10. a horn; 20. a paddle; 21. edge guiding; 22. carrying out edge following; 30. a read-write coil; 40. a reader-writer; 50. and detecting the conductor.
Detailed Description
In order that the invention may be readily understood, a more complete description of the invention will be rendered by reference to the appended drawings. Preferred embodiments of the present invention are shown in the drawings. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.
It will be understood that when an element is referred to as being "fixed to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "left," "right," and the like are used herein for illustrative purposes only.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and/or" as used herein includes any and all combinations of one or more of the associated listed items.
Example 1
Referring to fig. 1, the device for detecting the breaking of the propeller of the multi-rotor aircraft of the present invention is schematically shown, and comprises an electronic tag and a reader-writer 40, wherein the electronic tag is arranged in the propeller blade 20, and the reader-writer 40 is arranged on the horn 10. The multi-rotor aircraft pitch-breaking detection device is used for detecting the state of the paddle 20 on the driving shaft of the horn 10, and the motion path of the electronic tag is opposite to the reader-writer 40, so that the reader-writer 40 can perform contactless read-write operation on the electronic tag.
The electronic tag includes a read-write coil 30 and a detection conductor 50, wherein the detection conductor 50 is arranged along the blade root to the blade tip of the blade 20, and it should be noted that the detection conductor 50 is buried in the blade 20, and two ends of the detection conductor 50 are electrically connected to the read-write coil 30, and the read-write coil 30 and the detection conductor 50 form a circuit loop. When the paddle 20 is intact, the read-write coil 30 and the detection conductor 50 form a circuit loop, so that the reader-writer 40 can read information of the electronic tag, and the paddle 20 can be judged to be normal. When the paddle 20 is broken, the detection conductor 50 embedded in the paddle 20 breaks along with the breaking of the paddle 20, which causes the circuit loop formed by the read-write coil 30 and the detection conductor 50 to be broken, and the read-write device 40 cannot read and write the read-write coil 30, so that the paddle 20 can be judged to be broken.
Of course, the horn 10 or other positions of the aircraft are further provided with a data management device, the data management device is electrically connected to the reader/writer 40, the reader/writer 40 transmits the data read from the electronic tag to the data management device, and the data management device can decode and authenticate the read data. Specifically, the electronic tag further includes a storage unit, which is capable of storing data and is capable of being transmitted to the reader/writer 40 through the reader/writer antenna, the reader/writer coil 30 and the detection conductor 50 are connected in series.
In this embodiment, the storage unit may store information such as a production date and an enabling date of the paddle 20, and the data management device obtains the production date or the enabling date of the paddle 20 through the reader/writer 40 and the reading coil, so as to determine the remaining service life of the paddle 20. In addition, the storage unit may store the identity information of the paddle 20, and the data management device obtains the identity information of the paddle 20 through the reader/writer 40 and the reading coil, so as to determine whether the paddle 20 is mounted on the corresponding horn 10 or the driving shaft, so as to ensure that the paddle 20 is mounted correctly.
Through the design of the electronic tag and the reader-writer 40 of the multi-rotor aircraft broken-blade detection device, the specific blade 20 which is out of order on the aircraft can be accurately judged. In the existing multi-rotor aircraft, the flight control determines that the attitude of the aircraft is abnormal through a plurality of acceleration sensors on the aircraft, and the faulty blade 20 cannot be precisely positioned at all, so that the fault point cannot be isolated from the flight system. Especially two driving motor that set up in opposite directions on same horn 10, driving motor's drive shaft is provided with paddle 20, and the phenomenon of breaking the oar appears in paddle 20 on one of them driving motor, and the current many rotor crafts can't judge which driving motor on which horn 10 appears breaking the oar trouble, and then can't keep apart with the accurate shut down of the driving motor that appears breaking the oar. Based on the design of the electronic tag and the reader 40 of the multi-rotor aircraft pitch failure detection device, which driving motor has a pitch failure can be judged, and the data management equipment sends the driving motor information with the pitch failure to the flight control system of the aircraft, so that the flight control system can stop and isolate the driving motor with the pitch failure.
In order to detect the edge breakage phenomenon of the blade 20, the extending path of the detecting conductor 50 passes through the leading edge 21 and the trailing edge 22 of the blade 20, so that after the blade 20 is broken due to the impact, the detecting conductor 50 close to the leading edge 21 or the trailing edge 22 of the blade 20 breaks due to the edge breakage of the blade 20, and a circuit loop formed by the detecting conductor 50, the storage unit and the reading coil is broken, so that the data management equipment can judge that the blade 20 is abnormal, and the flight control system can shut down and isolate the driving motor with the fault of the blade 20, thereby preventing the damage of the blade 20 from further deteriorating and even leading to the occurrence of the situation of the blade breakage.
Example 2
The multi-rotor aircraft pitch-breaking detection device of the embodiment comprises an electronic tag and a reader-writer 40, wherein the electronic tag is arranged in a paddle 20, and the reader-writer 40 is arranged on a horn 10. The multi-rotor aircraft pitch-breaking detection device is used for detecting the state of the paddle 20 on the driving shaft of the horn 10, and the motion path of the electronic tag is opposite to the reader-writer 40, so that the reader-writer 40 can perform contactless read-write operation on the electronic tag.
The electronic tag includes a read-write coil 30 and a detection conductor 50, wherein the detection conductor 50 is arranged along the blade root to the blade tip of the blade 20, and it should be noted that the detection conductor 50 is buried in the blade 20, and two ends of the detection conductor 50 are electrically connected to the read-write coil 30, and the read-write coil 30 and the detection conductor 50 form a circuit loop. When the paddle 20 is intact, the read-write coil 30 and the detection conductor 50 form a circuit loop, so that the reader-writer 40 can read information of the electronic tag, and the paddle 20 can be judged to be normal. When the paddle 20 is broken, the detection conductor 50 embedded in the paddle 20 breaks along with the breaking of the paddle 20, which causes the circuit loop formed by the read-write coil 30 and the detection conductor 50 to be broken, and the read-write device 40 cannot read and write the read-write coil 30, so that the paddle 20 can be judged to be broken.
Specifically, the number of paddles 20 on each driving shaft is provided with a plurality of paddles, the paddles of the paddles 20 are connected through a connecting component, the read-write coil 30 is arranged in the connecting component, the read-write coil 30 is positioned on the rotating axis of the paddles 20, namely, a plurality of paddles 20 are arranged on each driving shaft, the paddles 20 on a single driving shaft share one read-write coil 30, and the read-write coil 30 is arranged inside the connecting component, so that the material cost of the read-write coil 30 can be reduced. In practical applications, when a blade 20 on a driving shaft fails, the driving shaft needs to be stalled and isolated, so that it is not actually necessary to precisely determine which blade 20 on the driving shaft fails, and only to know which driving shaft fails. Meanwhile, the read-write coil 30 is arranged on the rotation axis of the paddle 20, so that the reader-writer 40 can be always arranged opposite to the read-write coil 30, the reader-writer 40 can continuously read information of the electronic tag, and self-checking can be performed when the paddle 20 stops rotating.
Of course, the horn 10 or other positions of the aircraft are further provided with a data management device, the data management device is electrically connected to the reader/writer 40, the reader/writer 40 transmits the data read from the electronic tag to the data management device, and the data management device can decode and authenticate the read data. Specifically, the electronic tag further includes a storage unit, which is capable of storing data and is capable of being transmitted to the reader/writer 40 through the reader/writer antenna, the reader/writer coil 30 and the detection conductor 50 are connected in series.
In this embodiment, the storage unit may store information such as a production date and an enabling date of the paddle 20, and the data management device obtains the production date or the enabling date of the paddle 20 through the reader/writer 40 and the reading coil, so as to determine the remaining service life of the paddle 20. In addition, the storage unit may store the identity information of the paddle 20, and the data management device obtains the identity information of the paddle 20 through the reader/writer 40 and the reading coil, so as to determine whether the paddle 20 is mounted on the corresponding horn 10 or the driving shaft, so as to ensure that the paddle 20 is mounted correctly.
Through the design of the electronic tag and the reader-writer 40 of the multi-rotor aircraft broken-blade detection device, the specific blade 20 which is out of order on the aircraft can be accurately judged. In the existing multi-rotor aircraft, the flight control determines that the attitude of the aircraft is abnormal through a plurality of acceleration sensors on the aircraft, and the faulty blade 20 cannot be precisely positioned at all, so that the fault point cannot be isolated from the flight system. Especially two driving motor that set up in opposite directions on same horn 10, driving motor's drive shaft is provided with paddle 20, and the phenomenon of breaking the oar appears in paddle 20 on one of them driving motor, and the current many rotor crafts can't judge which driving motor on which horn 10 appears breaking the oar trouble, and then can't keep apart with the accurate shut down of the driving motor that appears breaking the oar. Based on the design of the electronic tag and the reader 40 of the multi-rotor aircraft pitch failure detection device, which driving motor has a pitch failure can be judged, and the data management equipment sends the driving motor information with the pitch failure to the flight control system of the aircraft, so that the flight control system can stop and isolate the driving motor with the pitch failure.
In addition, in order to facilitate replacement of the reading coil, the connection member is provided with grooves, and both ends of the detection conductor 50 are exposed to inner side walls of the grooves. The mounting seat is detachably arranged in the groove, the read-write coil 30 is arranged in the mounting seat, and the input end and the output end of the read-write coil 30 are exposed to the outer side wall of the mounting seat. The input end and the output end of the read-write coil 30 are respectively abutted against the two ends of the detection conductor 50, so that the electric connection between the read-write coil and the detection conductor 50 is realized. The read coil can be separated from the paddle 20 by removing the mounting. When the blade 20 breaks, the edge breaks, the intact reading coil can be recovered by detaching the mounting seat on the blade 20 for reuse.
Example 3
This embodiment differs from embodiment 2 in that: the number of paddles 20 on each driving shaft is provided with a plurality of paddles 20, one of the paddles 20 is provided with a read-write coil 30, the paddles of the paddles 20 are connected through a connecting part, a detection conductor 50 in the paddle 20 without the read-write coil 30 passes through the connecting part and is connected to the read-write coil 30, and the detection conductor 50 in the paddles 20 is connected in series with the read-write coil 30. That is, a plurality of paddles 20 are arranged on each driving shaft, only one paddle 20 is internally provided with a read-write coil 30, and the detection conductors 50 of other paddles 20 without the read-write coil 30 penetrate through the connecting component and are connected to the read-write coil 30 of the paddle 20 with the read-write coil 30, which can be understood as a read-write chip in which the paddles 20 share one paddle 20, so as to reduce the cost of the read-write coil 30.
Example 4
This embodiment differs from embodiment 2 in that: the read-write coil 30 is located at the paddle root of the paddle 20, and when a plurality of paddles 20 are disposed on each driving shaft, each paddle 20 is provided with one read-write coil 30. Correspondingly, the reader 40 of the arm 10 faces the motion track of the read-write coil 30. For each revolution of paddle 20, the read-write coil 30 of the paddle 20 passes through the reader-writer 40, and the reader-writer 40 can read and identify the electronic tag.
To facilitate replacement of the reading coil, the thrust surface of the blade root of the blade 20 is notched, and both ends of the detection conductor 50 are exposed to the inner side walls of the notch. The mounting seat is detachably arranged in the groove, the read-write coil 30 is arranged in the mounting seat, and the input end and the output end of the read-write coil 30 are exposed to the outer side wall of the mounting seat. The input end and the output end of the read-write coil 30 are respectively abutted against the two ends of the detection conductor 50, so that the electric connection between the read-write coil and the detection conductor 50 is realized. The read coil can be separated from the paddle 20 by removing the mounting. When the blade 20 breaks, the edge breaks, the intact reading coil can be recovered by detaching the mounting seat on the blade 20 for reuse.
Example 5
The difference between this embodiment and embodiment 1 is that the electronic tag includes a flexible printed board, a housing cavity is provided in the paddle 20, the flexible printed board is provided in the housing cavity, and the detecting conductor 50 is provided in the flexible printed board. Thereby positioning the sensing conductor 50 within the blade 20.
Example 6
To solve the same technical problems, this embodiment provides an aircraft, including a multi-rotor aircraft pitch-breaking detection device as described in each embodiment above.
In summary, the detecting conductor 50 is disposed along the blade root to the blade tip of the blade 20, and since the detecting conductor 50 and the reading coil are connected in series to form a circuit loop, when the blade 20 breaks, the detecting conductor 50 is disconnected along with the breaking of the blade 20, so that the circuit loop is broken, and the reader-writer 40 on the arm 10 cannot read the information through the reading coil, so that the occurrence of the breaking phenomenon can be determined.
The foregoing description is only illustrative of the present invention and is not intended to limit the scope of the invention, and all equivalent structures or equivalent processes or direct or indirect application in other related technical fields are included in the scope of the present invention.
Claims (10)
1. The utility model provides a disconnected oar detection device of many rotor crafts for detect the state of the epaxial paddle of drive of horn, its characterized in that, including locating electronic tags in the paddle and locate the reader-writer of horn, electronic tags includes read-write coil and detects the conductor, detect the conductor along the oar root of paddle is arranged to the oar point, just detect the both ends electricity of conductor connect in read-write coil, read-write coil and detect the conductor and constitute a circuit loop.
2. The multi-rotor aircraft pitch detection device of claim 1, wherein the detection conductor extends through the leading and trailing edges of the blade.
3. The multi-rotor aircraft pitch detection device of claim 1, wherein the electronic tag further comprises a memory unit, the read-write coil, and the detection conductor being connected in series.
4. The multi-rotor aircraft pitch-break detection device according to claim 1, wherein a plurality of paddles are provided on each of the drive shafts, the paddle roots of the plurality of paddles are connected by a connecting member, the read-write coil is provided in the connecting member, and the read-write coil is located on the rotation axis of the paddles.
5. The multi-rotor aircraft pitch-break detection device according to claim 1, wherein the number of the paddles on each of the drive shafts is plural and the read-write coil is provided in one of the paddles, the paddle roots of the plural paddles are connected by a connecting member, the detection conductors in the paddles not provided with the read-write coil pass through the connecting member and are connected to the read-write coil, and the detection conductors in the plural paddles are connected in series with the read-write coil.
6. The multi-rotor aircraft pitch detection device of claim 1, wherein the read-write coil is located at a pitch root of the blade.
7. The multi-rotor aircraft pitch detection device of claim 1, wherein the electronic tag comprises a flexible printed board, a receiving cavity is formed in the blade, the flexible printed board is arranged in the receiving cavity, and the detection conductor is arranged in the flexible printed board.
8. The multi-rotor aircraft pitch detection device according to claim 6, wherein the thrust surface of the blade root is provided with a groove, and both ends of the detection conductor are exposed to the inner side wall of the groove; the mounting seat is detachably arranged in the groove, the read-write coil is arranged in the mounting seat, and the input end and the output end of the read-write coil are exposed to the outer side wall of the mounting seat; the input end and the output end of the read-write coil are respectively abutted to the two ends of the detection conductor.
9. The multi-rotor aircraft pitch detection device according to claim 4, wherein the connecting member is provided with a groove, and both ends of the detection conductor are exposed to inner side walls of the groove; the mounting seat is detachably arranged in the groove, the read-write coil is arranged in the mounting seat, and the input end and the output end of the read-write coil are exposed to the outer side wall of the mounting seat; the input end and the output end of the read-write coil are respectively abutted to the two ends of the detection conductor.
10. An aircraft comprising a multi-rotor aircraft pitch break detection device according to any one of claims 1 to 9.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310176486.3A CN116161238A (en) | 2023-02-27 | 2023-02-27 | Multi-rotor aircraft broken-blade detection device |
| PCT/CN2024/078019 WO2024179351A1 (en) | 2023-02-27 | 2024-02-22 | Multi-rotor aircraft blade breakage detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310176486.3A CN116161238A (en) | 2023-02-27 | 2023-02-27 | Multi-rotor aircraft broken-blade detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116161238A true CN116161238A (en) | 2023-05-26 |
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ID=86421749
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310176486.3A Pending CN116161238A (en) | 2023-02-27 | 2023-02-27 | Multi-rotor aircraft broken-blade detection device |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN116161238A (en) |
| WO (1) | WO2024179351A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024179351A1 (en) * | 2023-02-27 | 2024-09-06 | 亿航智能设备（广州）有限公司 | Multi-rotor aircraft blade breakage detection device |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20130046858A (en) * | 2011-10-28 | 2013-05-08 | 엘에스전선 주식회사 | Monitoring system for wind turbine blade and monitoring method using the same |
| CN105116271B (en) * | 2015-08-07 | 2019-04-26 | 深圳一电航空技术有限公司 | Blade detection device and method, paddle components, aircraft and its control method |
| CN204964663U (en) * | 2015-08-07 | 2016-01-13 | 深圳一电科技有限公司 | Paddle detection device , paddle subassembly and aircraft |
| CN113302128A (en) * | 2020-08-24 | 2021-08-24 | 深圳市大疆创新科技有限公司 | Propeller abnormality detection method, unmanned aerial vehicle, control terminal, system and medium |
| CN113419194B (en) * | 2021-05-06 | 2022-05-20 | 湖南大学 | Real-time detection device and method for breakage of down lead of fan blade |
| CN116161238A (en) * | 2023-02-27 | 2023-05-26 | 亿航智能设备（广州）有限公司 | Multi-rotor aircraft broken-blade detection device |
-
2023
- 2023-02-27 CN CN202310176486.3A patent/CN116161238A/en active Pending
-
2024
- 2024-02-22 WO PCT/CN2024/078019 patent/WO2024179351A1/en unknown
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024179351A1 (en) * | 2023-02-27 | 2024-09-06 | 亿航智能设备（广州）有限公司 | Multi-rotor aircraft blade breakage detection device |
Also Published As
| Publication number | Publication date |
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| WO2024179351A1 (en) | 2024-09-06 |
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