Photoelectric device of optical fiber gyroscope

Abstract

The utility model discloses a photoelectric device of an optical fiber gyroscope. The photoelectric device comprises an optical fiber ring and a photoelectric device for microwave transmission, the optical fiber ring comprises a shielding case and an optical fiber arranged in the shielding case, the photoelectric device is fixed on the shielding case of the optical fiber ring through a fastener, the photoelectric device is connected with the optical fiber to form a loop, and positive and negative pins of the photoelectric device are respectively connected with the two Uamil wiring harnesses. The end parts of the two Uamil wiring harnesses are welded on the same side of a positive pin and a negative pin of the photoelectric device; the photoelectric device is mounted on the gyroscope, so that mechanical or short-circuit faults are avoided during working, and the working stability of the gyroscope is ensured.

Description

Technical Field

[0001] The utility model relates to the field of optoelectronic device design, in particular to an optoelectronic device for a fiber optic gyroscope. Background Technique

[0002] Optoelectronic devices are the core components in inertial navigation systems and are used in almost all vehicles, ships, and aircraft. The high precision, accuracy, and stability of the test data of Y-waveguides are key parameters for navigation systems. Especially for navigation systems used in the military, the insulation characteristics, reliability, and stability during use are crucial and play a decisive role in the service life of vehicles and aircraft. Currently, the Y-waveguide and the fiber optic loop of optoelectronic devices are connected by a 3M adhesive fixation method, with poor stability and a risk of falling off or detachment at any time. During installation, the consistency is poor, the process is complex, and the efficiency is low, resulting in low measurement accuracy of the Y-waveguide or even failure.

[0003] In addition, for the welding method of the Y-waveguide pins and the aerospace harness, a winding welding method is adopted. Since the distance between the positive and negative pins is 5 mm, the volume of the pins is large after winding welding, resulting in a reduction in the pin spacing, and even the pin spacing is less than the safe creepage distance. When the Y-waveguide is powered on, the creepage distance of the pins is too small, leading to breakdown and short circuit, and in severe cases, burning phenomena occur. Moreover, the welded parts of the pins are in a long-term exposed state, and the pins will oxidize and have poor contact, posing a great safety hazard. And stress is generated at the root of the aerospace harness after winding welding. When the Y-waveguide and the fiber optic loop undergo high and low temperature cycling and vibration tests with the gyroscope, the root of the harness will loosen or break, resulting in malfunctions or failures in the gyroscope tests. In severe cases, the gyroscope will be directly scrapped, causing quality accidents and raw material losses, affecting the delivery schedule of the gyroscope, and directly affecting the installation of military equipment. If the above risks always exist, even if it is qualified during the test process, the risks cannot be avoided during installation and use. The detachment of the Y-waveguide, short circuit of the pin welding, oxidation, and fracture of the root of the aerospace harness welding will directly lead to equipment failures, and in severe cases, fatal losses such as the fall of the aircraft will occur. Summary of the Utility Model

[0004] Aiming at the problems existing in the prior art, the utility model provides an optoelectronic device for a fiber optic gyroscope, which can effectively improve the stability of optoelectronic devices.

[0005] The utility model is realized through the following technical solutions:

[0006] An optoelectronic device for a fiber optic gyroscope includes a fiber optic loop and an optoelectronic device for microwave transmission;

[0007] The optical fiber loop includes a shielding cover and an optical fiber disposed inside thereof. The optoelectronic device is fixed on the shielding cover of the optical fiber loop by a fastener. The optoelectronic device is connected to the optical fiber to form a loop. The positive and negative pins of the optoelectronic device are respectively connected to two aerospace harnesses, and the ends of the two aerospace harnesses are welded to the same side of the positive and negative pins of the optoelectronic device.

[0008] Preferably, or, the two aerospace harnesses are respectively welded and fixed on the side where the positive and negative pins are away from each other.

[0009] Preferably, an insulating layer is provided on the pins and the ends of the aerospace harnesses.

[0010] Preferably, the insulating layer is a sleeve sleeved on the pins and the ends of the aerospace harnesses.

[0011] Preferably, the shielding cover includes a shielding cover body and cover plates provided at both ends thereof. The cover plates are connected to the shielding cover body, and the optical fiber is disposed on the surface of the shielding cover body.

[0012] Preferably, the optoelectronic device is fixed on the cover plate of the shielding cover by screws.

[0013] Preferably, the optoelectronic device is a Y waveguide. The Y waveguide is provided with three spaced-apart pins, namely a positive pin, a negative pin, and a ground pin.

[0014] Preferably, mounting holes are respectively provided on both sides of the three pins of the Y waveguide, and two threaded holes are provided on the cover plate of the shielding cover.

[0015] Preferably, the other end of the aerospace harness is connected to a gyroscope.

[0016] An optical fiber gyroscope includes the optoelectronic device described above.

[0017] Compared with the prior art, the present utility model has the following beneficial technical effects:

[0018] For the optoelectronic device of the optical fiber gyroscope provided by the present utility model, the optoelectronic device is fixed on the shielding housing of the optical fiber loop by a fastener, avoiding the risk of accidental dropping in the case of using an adhesive method, improving the operation stability of the optoelectronic device. Secondly, by controlling the positions of the aerospace harnesses on the positive and negative pins of the optoelectronic device, the two aerospace harnesses are located on the same side of the two pins, which can effectively increase the creepage distance between the two harnesses, solving the problem of breakdown and short circuit of the optoelectronic device due to too small creepage distance. In addition, during the welding process of the aerospace harness and the pin, the end of the aerospace harness is located on one side of the pin and welded. Compared with the fixing method of winding the harness and then welding, the internal stress on the pin is significantly reduced, improving the service life of the optoelectronic device. Description of the Drawings

[0019] Figure 1Structural schematic diagram of the optoelectronic device of the present utility model;

[0020] Figure 2 Schematic diagram of the pin connection between the aerospace cable and the Y waveguide of the present utility model;

[0021] Figure 3 Structural schematic diagram of the optical fiber loop of the present utility model;

[0022] Figure 4 Structural schematic diagram of the Y waveguide of the present utility model.

[0023] In the figure: 1, optical fiber loop; 2, threaded hole; 3, Y waveguide; 4, mounting hole; 5, screw; 6, aerospace cable; 7, positive and negative pins; 8, sleeve. Specific embodiments

[0024] The present utility model will be further described in detail below with reference to the accompanying drawings, which is an explanation rather than a limitation of the present utility model.

[0025] Refer to Figures 1-4 , an optoelectronic device of an optical fiber gyroscope, comprising an optical fiber loop and optoelectronic devices for microwave transmission;

[0026] The optical fiber loop includes a shielding cover and optical fibers arranged inside it. The optoelectronic devices are fixed on the shielding cover of the optical fiber loop through fasteners. The optoelectronic devices are connected to the optical fibers. The positive and negative pins of the optoelectronic devices are respectively connected to two aerospace cables. The ends of the two aerospace cables are welded on the same side of the positive and negative pins of the optoelectronic devices, or the two aerospace cables are respectively welded on the side where the positive and negative pins are far away from each other. Insulating layers are provided at the ends of the pins and the aerospace cables.

[0027] In some embodiments, the shielding cover of the optical fiber loop 1 is a barrel-shaped structure, including a shielding cover body and cover plates arranged at both ends thereof. The cover plates are connected to the shielding cover body, and the optical fibers are arranged on the surface of the shielding cover body.

[0028] The optical fibers are spirally arranged in sequence along the inner surface of the shielding cover body. The optical fibers are fixed on the surface of the shielding cover body by bonding. The bonding agent is optical fiber fixing glue. The two ends of the optical fibers are connected to the two ends of the optoelectronic devices to form a loop.

[0029] In some embodiments, the optoelectronic device is a Y waveguide 3. Three spaced pins 7 are arranged on one side of the Y waveguide 3, which are a positive pin, a negative pin, and a ground pin respectively. Optical fiber mounting holes 4 are provided at both ends of the Y waveguide 3, and the two ends of the optical fibers are inserted into the mounting holes.

[0030] On both sides of the three pins of the Y waveguide 3, mounting holes 4 are respectively provided. On the cover plate of the shielding cover, two threaded holes 2 are provided. Screws 5 pass through the mounting holes 4 to fix the Y waveguide 3 on the cover plate of the shielding cover, so as to achieve a stable connection between the Y waveguide 3 and the optical fiber ring.

[0031] Refer to Figure 2 , in order to increase the creepage distance between the two aerospace wire harnesses, the present application changes the existing method of winding the pins at the end of the wire harness and then welding. The two aerospace wire harnesses are arranged on the same side of the pins. At this time, the distance between the two aerospace wire harnesses is the pitch between the two pins. Then, the exposed ends of the aerospace wire harnesses are welded to the pins by welding, so that the creepage distance between the two aerospace wire harnesses meets the requirements.

[0032] In another embodiment, the two aerospace wire harnesses are respectively arranged on the mutually remote sides of the two pins. Refer to again Figure 2 , the aerospace wire harness on the positive pin is located on the right side of the pin, and the aerospace wire harness on the negative pin is located on the left side of the pin, that is, on the side close to the grounding pin, so as to maximize the creepage distance between the two aerospace wire harnesses.

[0033] The insulating layer is a sleeve 8, which is a heat-shrinkable sleeve. The sleeve is sleeved on the aerospace wire harness. After the end of the aerospace wire harness is welded to the pin, the sleeve is sleeved on the pin, and then heated to make it deformed, so as to form an insulating layer on the pin and the end of the aerospace wire harness.

[0034] Embodiment 1

[0035] An optoelectronic device of an optical fiber gyroscope includes a Y waveguide, an optical fiber ring, aerospace wire harnesses, and a transparent sleeve. The optical fiber is wound inside a cylindrical metal shielding cover. Cover plates are provided at both ends of the shielding cover and combined with the shielding cover to form an optical fiber ring 1. On the cover plate of the shielding cover of the optical fiber ring 1, there are 2 M2 threaded holes 2. On the Y waveguide 3, there are 2 mounting holes 4. Two M2 screws 5 pass through the mounting holes 4 on the Y waveguide 3 and are fastened in the threaded holes 2 on the optical fiber ring 1, so that the Y waveguide 3 is closely attached to the optical fiber ring 1. The wire skins of the two aerospace wire harnesses 6 are stripped by 5 mm, and the wire cores are respectively lapped and welded on the positive and negative pins 7 of the Y waveguide 3. The transparent sleeve 8 is inserted into the welding position from the other end of the aerospace wire harness 6, and the transparent sleeve 8 is heat-shrunk with a hot air gun to protect the welding position.

[0036] The working principle of an optoelectronic device of an optical fiber gyroscope is elaborated in detail as follows:

[0037] The Y waveguide is installed and fastened on the fiber optic ring with screws. Use a torque screwdriver to tighten the M2 screws to ensure that the installation torque meets the requirements of the M2 screws. Use wire cutters to cut two 0.08 mm2 Yuhang wire harnesses to a length of 100 mm. Use a hot stripper to strip both ends of the two 0.08 mm2 Yuhang wire harnesses to ensure that the wire cores are exposed 5 mm. Dip the soldering iron in solder and lap the Yuhang wire harness on the positive and negative pins to ensure that the soldering position is full and smooth with solder. Cut the transparent sleeve to 7 mm and thread it from the other end of the Yuhang wire harness to the soldering position. Use a hot air gun to blow the sleeve until it shrinks and tightly wraps the soldering part. The installation and soldering of the entire Y waveguide are completed.

[0038] Fuse the optical fibers on both sides of the Y waveguide with the optical fibers on the fiber optic ring to form a loop. Use fiber fixing glue to fix the optical fibers on the surface of the fiber optic ring. Install the optoelectronic device on the gyroscope. Solder the two Yuhang wire harnesses to the data acquisition board of the gyroscope. Power on the gyroscope. The Yuhang wire harnesses convert the electrical signals into digital signals, which are converted into optical signals through the Y waveguide for navigation testing. Finally, the Y waveguide converts the optical signals into digital signals, which are operated through the gyroscope acquisition board and the main control board to test the specific longitude, latitude, acceleration, heading, attitude and other data of equipment such as certain ships and aircraft. This installation and soldering method of the Y waveguide is simple, reliable and has good stability, ensuring the assembly efficiency and qualification rate of the gyroscope, and ensuring the stability, reliability and safety of the gyroscope when working on equipment such as ships and aircraft, enabling the equipment to perform precise positioning to obtain accurate positions and being able to conduct precise strikes more accurately in terms of strategy and tactics.

[0039] Embodiment 2

[0040] A gyroscope, including the optoelectronic device.

[0041] The above content is only to illustrate the technical idea of the present invention and cannot be used to limit the protection scope of the present invention. Any changes made on the basis of the technical solution according to the technical idea proposed by the present invention fall within the protection scope of the claims of the present invention.

Claims

1. An optoelectronic device of a fiber optic gyroscope, characterized in that: Includes fiber optic rings and optoelectronic devices for microwave transmission; The optical fiber ring includes a shielding cover and an optical fiber arranged inside the shielding cover. The optoelectronic device is fixed to the shielding cover of the optical fiber ring by fasteners. The optoelectronic device is connected to the optical fiber to form a loop. The positive and negative pins of the optoelectronic device are respectively connected to two space line cable bundles, and the ends of the two space line cable bundles are welded to the same side of the positive and negative pins of the optoelectronic device.

2. The optoelectronic device of a fiber optic gyroscope according to claim 1, characterized in that: Alternatively, the two space line harnesses are respectively welded and fixed on the sides where the positive and negative pins are away from each other.

3. The optoelectronic device of a fiber optic gyroscope according to claim 1, characterized in that: The pins and the ends of the spacecraft line harness are provided with an insulating layer.

4. The optoelectronic device of a fiber optic gyroscope according to claim 3, characterized in that: The insulating layer is a sleeve sleeved on the pins and the end of the spacecraft line harness.

5. The optoelectronic device of a fiber optic gyroscope according to claim 1, characterized in that: The shielding cover comprises a shielding cover body and cover plates arranged at two ends thereof, the cover plates are connected to the shielding cover body, and the optical fiber is arranged on the surface of the shielding cover body.

6. The optoelectronic device of a fiber optic gyroscope according to claim 5, characterized in that: The optoelectronic device is fixed on the cover plate of the shielding case by means of screws.

7. The optoelectronic device of a fiber optic gyroscope according to claim 1, characterized in that: The optoelectronic device is a Y waveguide, and the Y waveguide is provided with three pins arranged at intervals, namely a positive pin, a negative pin and a ground pin.

8. The optoelectronic device of a fiber optic gyroscope according to claim 7, characterized in that: Mounting holes are respectively arranged on both sides of the three pins of the Y waveguide, and two threaded holes are arranged on the cover plate of the shielding cover.

9. An optoelectronic device of a fiber optic gyroscope according to any one of claims 1 to 8, characterized in that: The other end of the spacecraft beam is connected to a gyroscope.

10. A fiber optic gyroscope, characterized in that: A photovoltaic device comprising any one of claims 1 to 9.

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