CN116182957B - Dynamic monitoring method for air release process of complex winding optical fiber coil - Google Patents
Dynamic monitoring method for air release process of complex winding optical fiber coil Download PDFInfo
- Publication number
- CN116182957B CN116182957B CN202310358630.5A CN202310358630A CN116182957B CN 116182957 B CN116182957 B CN 116182957B CN 202310358630 A CN202310358630 A CN 202310358630A CN 116182957 B CN116182957 B CN 116182957B
- Authority
- CN
- China
- Prior art keywords
- optical fiber
- coil
- fiber
- optical
- package
- 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.)
- Active
Links
Classifications
-
- 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
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M11/00—Testing of optical apparatus; Testing structures by optical methods not otherwise provided for
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M11/00—Testing of optical apparatus; Testing structures by optical methods not otherwise provided for
- G01M11/08—Testing mechanical properties
- G01M11/088—Testing mechanical properties of optical fibres; Mechanical features associated with the optical testing of optical fibres
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M11/00—Testing of optical apparatus; Testing structures by optical methods not otherwise provided for
- G01M11/30—Testing of optical devices, constituted by fibre optics or optical waveguides
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Optics & Photonics (AREA)
- Light Guides In General And Applications Therefor (AREA)
Abstract
The invention discloses a dynamic monitoring method for an air release process of a complex winding optical fiber coil, which comprises the steps of connecting two independently winding optical fiber coils end to end through a welding method, and fixing the two independently winding optical fiber coils on an aircraft; a central spindle of each optical fiber coil is provided with a universal device, and the tail optical fiber of each optical fiber coil is fixed through a fiber fixing device; the optical fiber tail ends of the two optical fiber packages respectively pass through the corresponding universal device and the corresponding fiber fixing device in sequence and then are connected to a distributed measurement system on the ground, the two optical fiber packages continuously and automatically release the optical fibers in the flying process to form a closed optical path, and the distributed strain or temperature in the released and unreleased optical fibers is dynamically monitored through the distributed measurement system. The method can obtain the actual strain distribution of each position of the optical fiber under the influence of the random factors of air flow when the optical fiber is stripped and released, and provides a basis for the optimal design of the complex winding optical fiber package structure.
Description
Technical Field
The invention belongs to an optical fiber package air release technology, and particularly relates to a dynamic monitoring method for an air release process of a complex winding optical fiber package.
Background
The optical fiber guidance is a wired remote control instruction guidance mode, and an information interaction bridge between the aerial vehicle and the ground control platform is established. Compared with a wireless guidance mode, the optical fiber guidance technology has the advantages of large transmission bandwidth, no delay, strong anti-interference capability, incapability of stealing information and the like, and is the optimal guidance mode of low-altitude aircrafts in the current and future battlefields. The optical fiber with a length of several kilometers is precisely wound according to a specified style to form an optical fiber coil with a high storage degree, and the optical fiber coil is stored in a narrow space at the tail of the aircraft, and after the aircraft takes off, the optical fiber is sequentially released from the surface of the optical fiber coil at a high speed, so that information is kept to be transmitted between the aircraft and a ground control platform.
The optical fiber is extremely complex in stress under the high-speed release state of 150m/s, including aircraft traction inertia, airflow resistance, gravity, coil viscous resistance and the like, the motion gesture of the optical fiber with a length of several kilometers changes sharply, phenomena such as stretching, bending, local friction and the like occur, stress abnormality is locally generated, and even the optical fiber with the diameter of millimeter breaks and fails, so that the aircraft is out of control. At present, in the development process of the optical fiber guidance technology, due to the lack of a corresponding dynamic monitoring method, the failure cause of the optical fiber in the air is difficult to locate, and the potential failure factor cannot be improved.
The difficulty of dynamically monitoring distributed parameters in the fiber release process is that: the distributed parameter measurement needs to connect the head and tail joints of the optical fiber of the coil into two ports of the test system at the same time, and the aerial release is the single-end release optical fiber of the coil, and the other optical fiber end is fixed in length, so that the release process of the optical fiber coil cannot be dynamically monitored due to the fact that a closed optical path which is lengthened when the optical fiber cannot be formed.
Disclosure of Invention
The invention aims to provide a dynamic monitoring method for an air release process of a complex winding optical fiber coil, which can obtain actual strain distribution of each position of an optical fiber under the influence of air flow random factors when the optical fiber is stripped and released and floating in the air, and provides a basis for the optimal design of the complex winding optical fiber coil structure.
The technical scheme adopted by the invention is that the dynamic monitoring method for the air release process of the complex winding optical fiber coil comprises the steps of connecting two independently winding optical fiber coils end to end through a welding method, and fixing the two independently winding optical fiber coils on an aircraft; a central spindle of each optical fiber coil is provided with a universal device, and the tail optical fiber of each optical fiber coil is fixed through a fiber fixing device; the optical fiber tail ends of the two optical fiber packages respectively pass through the corresponding universal device and the corresponding fiber fixing device in sequence and then are connected to a distributed measuring system on the ground, the optical fiber packages continuously and automatically release the optical fibers in the flying process to form a closed optical path, and the distributed strain or temperature in the released and unreleased optical fibers is dynamically monitored through the distributed measuring system.
The present invention is also characterized in that,
the optical fibers are released from the surface of the optical fiber coil in a circle-by-circle manner under the action of the tensile force, the direction is continuously adjusted through a universal device capable of freely rotating the end head of the optical fiber coil, the optical fiber is adapted to the changeable flight track of an aircraft, and the distance between the universal device and the end face of the optical fiber coil and the length of the universal device are required to meet the condition that the included angle between the released optical fibers and the core shaft of the optical fiber coil is always within the range of 0-30 degrees in the releasing process.
The two fiber fixing devices and the distributed measuring system are simultaneously fixed on the ground or placed on a ground movable platform, the length of the optical fiber between the two fiber fixing devices and the distributed measuring system is unchanged, and the length of the optical fiber between the optical fiber package and the corresponding fiber fixing device changes along with the real-time change of the flight track along with the continuous release of the optical fiber on the surface of the optical fiber package.
One of the two independent optical fiber packages is used as a companion flying package, the other optical fiber package is used as a measuring package, the tail ends of the two optical fiber packages are connected to a pulse light port of the distributed measuring system after passing through corresponding fiber fixing devices respectively, and the measuring package is connected to a detection light port of the distributed measuring system.
The fiber fixing device is an L-shaped bracket, and optical fibers of the two optical fiber packages are fixedly connected with the corresponding fiber fixing devices respectively.
The beneficial effects of the invention are as follows:
(1) The invention provides a dynamic monitoring method for an aerial release process of a complex winding optical fiber coil, which is used for acquiring distributed parameters in an optical fiber in real time in the process of carrying the optical fiber package by an aircraft and releasing the optical fiber in a high-speed flight manner, so that the problem that a closed optical path cannot be formed by the existing single-wire package release is solved.
(2) The method of the invention provides that the optical fibers of the two coils are connected end to end and are fixed on an aircraft at the same time, the optical fibers are synchronously released in the flying process, the tail ends of the optical fibers of the two coils are respectively connected into a ground distributed measuring system, thereby forming a time-variable optical fiber loop, and the strain or the temperature distribution of each position of the released optical fibers and unreleased optical fibers is monitored in real time in the process of releasing the coils, so as to provide measuring data for the research and development of the optical fiber guidance technology. The method can obtain the actual strain distribution of each position of the optical fiber under the influence of the random factors of air flow when the optical fiber is stripped and released, and provides a basis for the optimal design of the complex winding optical fiber package structure.
(3) The method provides a high-speed releasing mode of the optical fiber from the complex winding coil, the released optical fiber automatically adapts to the changeable track of the aircraft, and the problems that the optical fiber at the edge of the coil is easy to collapse and the optical fiber is easy to break when being stripped from the coil are solved.
(4) The dynamic monitoring method for the optical fiber package air release process provided by the invention can obtain the actual strain distribution of each position of the optical fiber under the influence of air flow random factors when the optical fiber is stripped and released, and provides a basis for the optimal design of the complex winding optical fiber package structure.
Drawings
FIG. 1 is a schematic geometric cross-sectional view of a complex wound fiber optic package of the present invention;
FIG. 2 is a schematic diagram of a dual-wire packet sync release according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of fiber release during high speed flight of an aircraft in accordance with an embodiment of the present invention;
FIG. 4 illustrates an example two-wire packet sync release;
FIG. 5 shows the strain distribution measured in real time for a released section of the measuring coil of the present invention;
FIG. 6 is a graph of the distribution of strain around the instant of fiber stripping on a measurement package of the present invention.
In the figure, 1, the diameter of an optical fiber, 2, the number of unwinding turns, 3, the inner diameter of the end face of a coil, 4, the length of the coil, 5, the outer diameter of the end face of the coil, 6, the winding of the coil on a first layer, 7, the unmanned aerial vehicle, 8, the accompanying coil, 9, a first fiber fixer, 10, a distributed measuring system, 11, a second fiber fixer, 12, the propagation direction of probe light, 13, the measuring coil, 14, the release direction of the optical fiber, 15, a universal device and 16, the released optical fiber.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The invention provides a dynamic monitoring method for an air release process of a complex winding optical fiber coil, which comprises the steps of connecting two independently winding optical fiber coils end to end through a welding method, and fixing the two independently winding optical fiber coils on an aircraft; a central spindle of each optical fiber coil is provided with a universal device 15, and the tail optical fiber of each optical fiber coil is fixed by a fiber fixing device; the optical fiber tail ends of the two optical fiber packages respectively pass through the corresponding universal device 15 and the corresponding fiber fixing device in sequence and then are connected to the distributed measurement system 10 on the ground, the two optical fiber packages continuously and automatically release the optical fibers in the flying process to form a closed optical path, and the distributed strain or temperature in the released and unreleased optical fibers is dynamically monitored through the distributed measurement system 10.
When the optical fiber coil flies along with the aircraft, the optical fibers are released from the surface of the coil one by one under the action of tension, the direction is continuously adjusted through the universal device 15 which is freely rotated at the end of the coil, the optical fiber coil is adapted to the changeable flight track of the aircraft, the optical fibers which are not released are prevented from being rubbed by the released optical fibers, so that the edge of the coil is prevented from collapsing simultaneously, the distance between the universal device 15 and the end face of the optical fiber coil and the length of the universal device 15 are required to meet that the included angle between the released optical fibers and the core shaft of the coil is always within the range of 0-30 degrees in the releasing process.
The two fiber fixing devices and the distributed measuring system 10 are simultaneously fixed on the ground or placed on a ground movable platform, the length of the optical fiber between the two fiber fixing devices and the distributed measuring system 10 is unchanged, and the length of the optical fiber between the optical fiber package and the corresponding fiber fixing device changes along with the real-time change of the flight track along with the continuous release of the optical fiber on the surface of the optical fiber package.
The distributed measurement system is a brillouin distributed measurement system; one of the two independent optical fiber packages is used as a companion fiber package 8, the other optical fiber package is used as a measuring package 13, the companion fiber package 8 is connected to a pulse light port of the distributed measuring system 10 after the tail ends of the two optical fiber packages pass through corresponding fiber fixing devices respectively, and the measuring package 13 is connected to a detection light port of the distributed measuring system 10.
The fiber fixing device is an L-shaped bracket, and optical fibers of the two optical fiber packages are fixedly connected with the corresponding fiber fixing devices respectively.
Example one.
The present example selects an optical fiber coil with a geometric cross section as shown in fig. 1 to illustrate a dynamic monitoring method for the air release process of the complex winding optical fiber coil, and is not limited to the present example, and the aircraft used in the present example is the unmanned aerial vehicle 7.
The quartz optical fiber with the optical fiber diameter of 1mm is wound layer by layer to form an optical fiber package, as shown in fig. 1, the number of turns of each layer is reduced by 3 turns compared with that of the upper layer in the winding process, namely the unwinding number of turns 2 is 3 turns; the inner diameter 3 of the end face of the coil is 20cm, the outer diameter 5 of the end face of the coil is 25cm, the length 4 of the coil is 35cm, and the total length of each coil optical fiber is 3.5km. The optical fiber head end in the optical fiber coil is positioned at the first layer 6, namely the innermost layer, of the coil winding, and the tail end is positioned at the outermost layer of the winding.
The head ends of two identical optical fiber coils are connected with the head end through an optical fiber fusion splicer, and the two optical fiber coils and the optical fiber connecting section between the two optical fiber coils are all fixed below wings on two sides of the unmanned aerial vehicle 7, as shown in fig. 2, wherein one coil serves as a fly coil 8, and the other coil serves as a measuring coil 13. The tail ends of the two optical fiber packages respectively pass through the first optical fiber fixing device 9 and the second optical fiber fixing device 11 on the ground and are connected into a pulse light port and a detection light port of the distributed measurement system 10 to form a closed light path, the optical fiber releasing direction 14 is opposite to the flight direction of the unmanned aerial vehicle, and the detection light propagation direction 12 is transmitted from the detection light port along the direction of the measurement package 13-the accompanying package 8-the pulse light port, wherein the distributed measurement system 10 is a Brillouin distributed measurement system. The two fiber fixing devices respectively fix the two optical fibers, the positions of the two fiber fixing devices are kept unchanged, the two fiber fixing devices and the distributed measurement system 10 are all arranged on the ground, the unmanned aerial vehicle 7 carries the two wire packages to fly forwards at the speed of 150m/s, and the released optical fibers are released from the surface of the wire packages point by point under the action of tension. Because the two coils release the optical fibers independently and the length of the optical fibers between the two coils and the ground fiber fixing device is changed at any time, the distributed strain and the temperature in the coils can be measured in real time. The technology of the brillouin test system for measuring distributed strain and temperature in the optical fiber in a static manner on the ground is commercialized, and the dynamic monitoring method of the air release process of the optical fiber package is mainly described.
When the optical fiber coil flies along with the aircraft 7, the optical fibers are released from the surface of the coil in turns under the action of tension, and the direction is continuously adjusted through the universal device 15 with the freely rotating coil end head, so that the optical fiber coil is suitable for the changeable flight track of the aircraft, as shown in fig. 3. The general shape of the optical fiber coil is approximately conical, the inner diameter of the end face of the coil is 20cm, the outer diameter of the end face of the coil is 25cm at the maximum, and in order to avoid the interference of the released optical fiber to the optical fiber with the undetached edge of the coil, the condition should be satisfied: the angle θ between the released optical fiber 16 and the spool is always in the range of 0-30 ° during the release process. Accordingly, the distance a of the gimbal from the end face of the package and the length b of the gimbal are designed, in this example, the maximum included angle between the released optical fiber 16 and the core shaft of the package is located in the first layer on the right side of the optical fiber package, the minimum included angle between the released optical fiber and the core shaft of the package is located in the outermost layer on the left side of the package, and the following constraint condition is established:
considering the size of the installation position, the distance a is 6cm, b is more than or equal to 25cm, and b is 27cm.
When the optical fiber package flies, a Brillouin distributed measuring system is arranged, the pumping light power is 50mW, the detection light power is 30mW, the optical fiber distributed strain is measured in real time, the optical fiber stress distribution floating in 3km space-time is released as shown in figure 5, larger strain is generated at the moment that the optical fiber is stripped from the package near the position of 2.1km, and the length of the stripped optical fiber is influenced by the stripped optical fiber near the near field by about 200m, as shown in figure 6.
Example two
The difference between this example and example one is that a single wire package is secured to the aircraft and another wire package is secured to the ground, as shown in fig. 4, the remainder being the same as example one described above.
The two identical coils are connected end to end, the accompanying flight coil is fixed on the ground fiber fixer, the test coil is fixed below the unmanned aerial vehicle wing, and when the flight starts, the accompanying flight coil reversely releases the optical fiber, so that the accompanying flight optical fiber between the accompanying flight optical fiber and the unmanned aerial vehicle is always kept in a loose state.
Example three
The difference between the first embodiment and the first embodiment is that the ground fiber fixing device and the distributed measurement system are both arranged on the ground mobile trolley, and the ground fiber fixing device and the distributed measurement system are suitable for remote air investigation of unmanned aerial vehicles.
Example four
The difference between the present example and examples one, two and three is that the distributed measurement system measures the temperature distribution of the optical fiber and the floating optical fiber in the package in real time during the air flight.
Claims (2)
1. The dynamic monitoring method for the air release process of the complex winding optical fiber coil is characterized in that two independently wound optical fiber coils are connected end to end through a welding method, and the two independently wound optical fiber coils are fixed on an aircraft; a universal device (15) is arranged on the mandrel of each optical fiber coil, and the tail optical fiber of each optical fiber coil is fixed through a fiber fixing device; the tail ends of the optical fibers of the two optical fiber packages respectively pass through the corresponding universal device (15) and the corresponding fiber fixing device in sequence and then are connected to a distributed measuring system (10) on the ground, the two optical fiber packages continuously and automatically release the optical fibers in the flying process to form a closed optical path, and the distributed strain or temperature in the released and unreleased optical fibers is dynamically monitored through the distributed measuring system (10);
the optical fibers are released from the surface of the optical fiber coil in a circle-by-circle way under the action of the tensile force, the direction is continuously adjusted through a universal device (15) with the end of the optical fiber coil freely rotating, the optical fiber is adapted to the changeable flight track of an aircraft, and the distance between the universal device (15) and the end face of the optical fiber coil and the length of the universal device (15) are required to meet the condition that the included angle between the released optical fibers and the core shaft of the optical fiber coil is always within the range of 0-30 degrees in the releasing process;
the two fiber fixing devices and the distributed measuring system (10) are simultaneously fixed on the ground or placed on a ground movable platform, the length of the optical fiber between the two fiber fixing devices and the distributed measuring system (10) is unchanged, and the length of the optical fiber between the optical fiber package and the corresponding fiber fixing device changes along with the real-time change of the flight track along with the continuous release of the optical fiber on the surface of the optical fiber package;
one of the two independent optical fiber packages is used as a companion fiber package (8), the other optical fiber package is used as a measurement package (13), after the tail ends of the two optical fiber packages pass through corresponding fiber fixing devices respectively, the companion fiber package (8) is connected to a pulse light port of the distributed measurement system (10), and the measurement package (13) is connected to a detection light port of the distributed measurement system (10).
2. The method for dynamically monitoring the air release process of a complex wound optical fiber coil according to claim 1, wherein the fiber fixing device is an L-shaped bracket, and optical fibers of two optical fiber coils are fixedly connected with the corresponding fiber fixing devices respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310358630.5A CN116182957B (en) | 2023-04-06 | 2023-04-06 | Dynamic monitoring method for air release process of complex winding optical fiber coil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310358630.5A CN116182957B (en) | 2023-04-06 | 2023-04-06 | Dynamic monitoring method for air release process of complex winding optical fiber coil |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116182957A CN116182957A (en) | 2023-05-30 |
| CN116182957B true CN116182957B (en) | 2023-09-19 |
Family
ID=86452305
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310358630.5A Active CN116182957B (en) | 2023-04-06 | 2023-04-06 | Dynamic monitoring method for air release process of complex winding optical fiber coil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116182957B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104614017A (en) * | 2015-01-22 | 2015-05-13 | 国家电网公司 | Distributed strain and stress monitoring method of electric aerial optical cables based on double-tube special-shaped structure |
| CN109693813A (en) * | 2019-01-30 | 2019-04-30 | 西安工业大学 | A kind of ground simulation actinobacillus device being compatible with more specification spools |
| CN209275854U (en) * | 2018-10-31 | 2019-08-20 | 东莞天速通信技术有限公司 | A kind of aircraft testing agency |
| CN113836711A (en) * | 2021-09-15 | 2021-12-24 | 北京航空航天大学 | Light-making optical fiber winding modeling method |
| CN115716549A (en) * | 2022-11-08 | 2023-02-28 | 南通大学 | Unmanned aerial vehicle flying with charging wire and working method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11286773B2 (en) * | 2020-03-11 | 2022-03-29 | Neubrex Co., Ltd. | Using fiber-optic distributed sensing to optimize well spacing and completion designs for unconventional reservoirs |
-
2023
- 2023-04-06 CN CN202310358630.5A patent/CN116182957B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104614017A (en) * | 2015-01-22 | 2015-05-13 | 国家电网公司 | Distributed strain and stress monitoring method of electric aerial optical cables based on double-tube special-shaped structure |
| CN209275854U (en) * | 2018-10-31 | 2019-08-20 | 东莞天速通信技术有限公司 | A kind of aircraft testing agency |
| CN109693813A (en) * | 2019-01-30 | 2019-04-30 | 西安工业大学 | A kind of ground simulation actinobacillus device being compatible with more specification spools |
| CN113836711A (en) * | 2021-09-15 | 2021-12-24 | 北京航空航天大学 | Light-making optical fiber winding modeling method |
| CN115716549A (en) * | 2022-11-08 | 2023-02-28 | 南通大学 | Unmanned aerial vehicle flying with charging wire and working method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 基于BOTDR的传感光纤固定方式研究;刘永莉;孙红月;尚岳全;于洋;;传感技术学报(第09期);第1353-1358页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116182957A (en) | 2023-05-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5729966A (en) | Method of marking optical fiber lay direction reversal points on cable jackets | |
| CN101915576B (en) | Optical fiber loop for optical fiber gyroscope | |
| US9676496B2 (en) | Ground station with shuttled drum for tethered aerial vehicles | |
| US9057815B2 (en) | Angular alignment of optical fibers for fiber optic ribbon cables, and related methods | |
| US20150375852A1 (en) | Plastic Optical Fiber for Reliable Low-Cost Avionic Networks | |
| US9429954B2 (en) | Flight control for an airborne wind turbine | |
| JPH04219705A (en) | Optical fiber | |
| EP3084211A1 (en) | Systems and apparatus for cable management | |
| CN102103228B (en) | Double waveguide parallel polarization maintaining fiber and manufacturing method thereof | |
| CN116182957B (en) | Dynamic monitoring method for air release process of complex winding optical fiber coil | |
| WO2018223499A1 (en) | Optical fibre cable with optical fibre sensing and communication functions, and manufacturing method therefor | |
| CN109867154A (en) | One kind three drives coating roll equipment robust control method | |
| CN110926505B (en) | Optical fiber ring winding method for improving stress distribution symmetry of optical fiber ring | |
| CN113510747A (en) | In-situ detection robot for aero-engine blade and movement method thereof | |
| CN207046566U (en) | A kind of flutter wind tunnel test model refueling hose Automatic-expanding system | |
| CN103968820A (en) | Device for winding fiber-optic ring of fiber-optic gyroscope and method of device | |
| US9352930B2 (en) | Methods and systems for winding a tether | |
| US4996420A (en) | Measurement of optical attenuation along the length of bent optical fibers | |
| CN103063898B (en) | Sensing optical fiber ring and all-fiber current transformer | |
| CN203011982U (en) | Sensing optical fiber ring and all-fiber current transformer | |
| CN201837395U (en) | Optical fiber loop for optical fiber peg-top | |
| CN201896000U (en) | Wire looping device | |
| CN103063897B (en) | Sensing optical fiber coil and anti-vibration all-fiber current transformer | |
| CN110589631A (en) | Unmanned aerial vehicle mooring cable winding and unwinding control system and control method | |
| CN111351634B (en) | Method for detecting load-bearing retraction performance of photoelectric composite cable |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |