Auxiliary fiber threading device for spaceflight fiber MT ferrule

Abstract

The utility model provides a kind of astronavigation optical fiber MT ferrule auxiliary fiber insertion device, including clamping base and clamping cover, clamping cover can be folded and installed on clamping base;Clamping base is provided with fixed groove, fixed groove includes the optical fiber sheath fixed groove in rear portion and the multiple optical fiber cladding fixed groove in front portion, the size and interval of optical fiber cladding fixed groove are matched with MT ferrule;Optical fiber sheath fixed groove is used to accommodate the optical fiber sheath of multiple parallel optical fibers, and the multiple optical fiber cladding fixed groove is arranged in parallel, for accommodating the optical fiber cladding of multiple stripping optical fiber sheaths.The utility model can realize the independent fixing of sheath and cladding by sheath and cladding fixed groove, the size and interval of optical fiber cladding fixed groove are matched with MT ferrule, effectively avoid the problem of brittle fracture caused by insufficient precision, and the cooperation design of sheath and cladding fixed groove can accurately control the radial position and interval of each optical fiber, ensure that optical fiber array and MT ferrule hole site are matched with high precision.

Description

Technical Field

[0001] This utility model relates to the field of aerospace optical cable assembly technology, specifically to an aerospace optical fiber MT ferrule auxiliary fiber threading device. Background Technology

[0002] With the increasing demand for high-throughput data transmission in spacecraft, the application of optical cable assemblies is becoming more widespread, and the processing technology of aerospace optical cables is also constantly developing. Here, aerospace optical cable specifically refers to a multimode 12-core optical cable assembled with a 12-core MT ferrule. In the civilian optical cable field, fixing is mainly achieved through tooling or fast-curing adhesives. This fixing method constrains the position of the optical fiber by fixing the cable sheath, but the mismatch between the sheath and the optical fiber is poor, making complete fixation impossible. During fiber insertion, the instability of the fiber fixation leads to high difficulty in matching it with the optical connector, easily resulting in fiber breakage or insertion failure. Therefore, there is an urgent need in this field for a high-matching fiber insertion auxiliary fixing device. Utility Model Content

[0003] In view of the deficiencies in the existing technology, the purpose of this utility model is to provide an auxiliary fiber threading device for aerospace fiber optic MT ferrules.

[0004] The aerospace fiber optic MT ferrule auxiliary fiber threading device provided by this utility model includes a clamping base and a clamping cover plate, wherein the clamping cover plate can be folded and installed on the clamping base. The clamping base is provided with a fixing groove, which includes a fiber sheath fixing groove at the rear and a plurality of fiber cladding fixing grooves at the front. The size and spacing of the fiber cladding fixing grooves are matched with the MT ferrule. The fiber sheath fixing slot is used to accommodate the fiber sheath of multiple parallel optical fibers. Multiple fiber cladding fixing slots are arranged in parallel to accommodate the fiber cladding of multiple stripped optical fibers in a one-to-one correspondence.

[0005] Preferably, the upper surface of the clamping base is provided with a quick-locking component; The quick-lock component is located on one side of the fixing groove and is used to lock the clamping cover plate when it is closed.

[0006] Preferably, the clamping cover plate includes a magnetic metal cover plate, and the quick-lock component includes a magnet, which is fixedly installed in the mounting groove on the upper surface of the clamping base.

[0007] Preferably, when the optical fiber cladding is inserted into the optical fiber cladding fixing groove, the gap between the optical fiber cladding and the inner wall of the optical fiber cladding fixing groove is set.

[0008] Preferably, the diameter of the fiber cladding fixing groove is equal to the outer diameter of the fiber cladding plus 2 micrometers.

[0009] Preferably, the front end of the fiber optic sheath fixing groove is a plane perpendicular to the length direction of the fiber, used to abut against the front ends of multiple fiber optic sheaths.

[0010] Preferably, the width of the optical fiber sheath fixing groove is equal to the sum of the widths of the multiple optical fiber sheaths.

[0011] Preferably, when the clamping cover is closed, the distance between the lower surface of the clamping cover and the bottom of the optical fiber sheath fixing groove is equal to the height of the optical fiber sheath. The lower surface of the clamping cover plate forms a clamping part with the bottom of the optical fiber sheath fixing groove, which is used to clamp the optical fiber sheath.

[0012] Preferably, one side of the fiber sheath fixing groove is connected to one side of the fiber cladding fixing groove, the other side of the fiber sheath fixing groove extends to one side of the clamping base, and the other side of the fiber cladding fixing groove extends to the other side of the clamping base.

[0013] Preferably, the length of the fiber cladding fixing groove is no more than 7 mm.

[0014] Compared with the prior art, the present invention has the following beneficial effects: This invention enables independent fixing of the sheath and cladding through the sheath and cladding fixing groove. The size and spacing of the fiber optic cladding fixing groove match the MT ferrule, effectively avoiding the brittle fracture problem caused by insufficient precision in the traditional overall fixing method. Furthermore, the cooperative design of the sheath and cladding fixing groove can precisely control the radial position and spacing of each fiber, ensuring a high-precision match between the fiber array and the MT ferrule hole. Attached Figure Description

[0015] Other features, objects, and advantages of this invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a schematic diagram illustrating the working principle of this utility model.

[0016] The diagram shows: Detailed Implementation

[0017] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0018] This utility model discloses an auxiliary fiber insertion device for aerospace fiber optic MT ferrules. The device enables independent fixing of the sheath and cladding through the sheath and cladding fixing groove. The size and spacing of the fiber optic cladding fixing groove match the MT ferrule, effectively avoiding the brittle fracture problem caused by insufficient precision in the traditional overall fixing method. Furthermore, the cooperative design of the sheath and cladding fixing groove can accurately control the radial position and spacing of each fiber, ensuring a high-precision match between the fiber array and the MT ferrule hole position.

[0019] According to the aerospace fiber optic MT ferrule auxiliary fiber insertion device provided by this utility model, such as Figure 1 As shown, the device includes a clamping base 2 and a clamping cover plate 1. The clamping cover plate 1 can be folded and installed on the clamping base 2. The clamping base 2 is provided with fixing grooves, including a fiber sheath fixing groove 4 located at the rear and multiple fiber cladding fixing grooves 5 located at the front. The size and spacing of the fiber cladding fixing grooves 5 match the MT ferrule. The fiber sheath fixing groove 4 is used to accommodate fiber sheaths 6 of multiple parallel fibers. The multiple fiber cladding fixing grooves 5 are arranged side by side to accommodate multiple fiber claddings 7 after the fiber sheaths 6 have been stripped in a one-to-one correspondence. Preferably, the length of the fiber cladding fixing groove 5 is no more than 7 mm. Figure 2 As shown, during fiber insertion, the fiber sheath fixing groove 4 and the fiber cladding fixing groove 5 can stably fix the fiber sheath 6 and the fiber cladding 7 respectively, thereby ensuring the stability of the MT ferrule during fiber insertion.

[0020] When the fiber cladding 7 is inserted into the fiber cladding fixing groove 5, a gap is formed between the fiber cladding 7 and the inner wall of the fiber cladding fixing groove 5. Preferably, the diameter of the fiber cladding fixing groove 5 is equal to the outer diameter of the fiber cladding 7 plus 2 micrometers. The front end of the fiber sheath fixing groove 4 is a plane perpendicular to the length direction of the fiber, used to abut against the front ends of multiple fiber sheaths 6. The width of the fiber sheath fixing groove 4 is equal to the sum of the widths of the multiple fiber sheaths 6. Specifically, one side of the fiber sheath fixing groove 4 is connected to one side of the fiber cladding fixing groove 5, the other side of the fiber sheath fixing groove 4 extends to one side of the clamping base 2, and the other side of the fiber cladding fixing groove 5 extends to the other side of the clamping base 2.

[0021] In a preferred embodiment, a quick-locking member 3 is provided on the upper surface of the clamping base 2; the quick-locking member 3 is located on one side of the fixing groove and is used to lock the clamping cover 1 when it is closed. The clamping cover 1 includes a magnetic metal cover plate, and the quick-locking member 3 includes a magnet, which is fixedly installed in the mounting groove on the upper surface of the clamping base 2. The clamping cover 1 is clamped by attracting the magnet on the clamping base 2. When the clamping cover 1 is closed, the distance between the lower surface of the clamping cover 1 and the bottom of the optical fiber sheath fixing groove 4 is equal to the height of the optical fiber sheath 6; a clamping part is formed between the lower surface of the clamping cover 1 and the bottom of the optical fiber sheath fixing groove 4 for clamping the optical fiber sheath 6.

[0022] Example 1 This embodiment discloses an aerospace fiber optic MT ferrule auxiliary fiber threading device, including: a clamping base 2, a clamping cover plate 1, and a quick-lock component 3; the clamping base 2 includes a fiber sheath fixing groove 4 and a fiber cladding fixing groove 5, the width of the fiber sheath fixing groove 4 is equal to the width of 12 fibers with tight sheaths laid flat, and the diameter of the fiber cladding fixing groove 5 is equal to the outer diameter of the fiber cladding 7 plus 2 micrometers. The clamping cover 1 is made of magnetic metal to achieve the attraction between the cover and the clamping base 2; The quick-lock component 3 is a strong magnetic magnet used to engage with the clamping cover plate 1; The quick-connect component 3 and the clamping base 2 are connected by an interference fit; this is used to firmly connect the magnet to the base plate. The aforementioned aerospace optical fiber is a radiation-resistant optical fiber with a cladding outer diameter of 125 μm; The aerospace optical fiber is a stripped optical fiber with a stripped length of not less than 7mm. The aerospace optical fibers are arranged in a specific order and placed into the fixing slots. The end face of the optical fiber sheath 6 is kept flush and placed at the junction of the optical fiber sheath fixing slot 4 and the optical fiber cladding fixing slot 5. Insert the stripped aerospace optical fibers one by one into the channel, fixing the fiber positions so that the spacing between them is completely consistent with the fiber aperture of the MT ferrule. This facilitates the simultaneous insertion of multiple fibers into the ferrule. The specific fiber insertion steps are as follows: Step 1: Strip 7mm~10mm of the optical fiber. The optical fiber is stripped by hot stripping to remove the sheath and coating. The stripped end face is kept flush. Step 2: Insert the optical fibers into the fixing slots in the required order, with the heat-stripped end face at the junction of the optical fiber sheath fixing slot 4 and the optical fiber cladding fixing slot 5, and the optical fibers are neatly arranged. Step 3: Flip the clamping cover 1 so that the clamping cover 1 and the clamping base 2 are attracted to each other; Step 4: Align the clamped optical fiber with the tail of the MT ferrule and confirm through the observation hole that each optical fiber is in the MT ferrule channel. Step 5: Slowly insert the optical fiber, open the clamping cover 1, and remove the auxiliary device; Step 6: Continue inserting the second half of the optical fiber to complete the fiber threading.

[0023] This invention enables rapid fiber threading and quality assurance during the development of aerospace optical cable assemblies, solves the problem of difficult fiber threading of multi-core optical fibers, uses ferromagnetic metal as a cover plate, and is attracted by strong magnets, making it convenient to use and reliable to fix. Moreover, for different types and specifications of optical fibers, only the size of the fixing slot needs to be modified, making the method universal. The fiber fixing length of the fiber threading device is greater than 5mm, and the end of the fiber is kept vertical to achieve the purpose of position matching.

[0024] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0025] The specific embodiments of this utility model have been described above. It should be understood that this utility model is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the substantive content of this utility model. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A fiber optic MT ferrule-assisted fiber insertion device for aerospace applications, characterized in that, Includes a clamping base (2) and a clamping cover plate (1), wherein the clamping cover plate (1) can be folded and installed on the clamping base (2); The clamping base (2) is provided with a fixing groove, which includes a fiber sheath fixing groove (4) located at the rear and a plurality of fiber cladding fixing grooves (5) located at the front. The size and spacing of the fiber cladding fixing grooves (5) are matched with the MT ferrule. The fiber sheath fixing slot (4) is used to accommodate the fiber sheath (6) of multiple parallel optical fibers, and multiple fiber cladding fixing slots (5) are arranged in parallel to accommodate the fiber cladding (7) of multiple stripped fiber sheaths (6) in a one-to-one correspondence.

2. The aerospace fiber optic MT ferrule-assisted fiber insertion device according to claim 1, characterized in that, The upper surface of the clamping base (2) is provided with a quick-lock component (3); The quick-locking component (3) is located on one side of the fixing groove and is used to lock the clamping cover (1) when the clamping cover (1) is closed.

3. The aerospace fiber optic MT ferrule auxiliary fiber insertion device according to claim 2, characterized in that, The clamping cover plate (1) includes a magnetic metal cover plate, and the quick-lock component (3) includes a magnet, which is fixedly installed in the mounting groove on the upper surface of the clamping base (2).

4. The aerospace fiber optic MT ferrule auxiliary fiber insertion device according to claim 1, characterized in that, When the optical fiber cladding (7) is inserted into the optical fiber cladding fixing groove (5), the gap between the optical fiber cladding (7) and the inner wall of the optical fiber cladding fixing groove (5) is set.

5. The aerospace fiber optic MT ferrule auxiliary fiber insertion device according to claim 4, characterized in that, The diameter of the fiber cladding fixing groove (5) is equal to the outer diameter of the fiber cladding (7) plus 2 micrometers.

6. The aerospace fiber optic MT ferrule auxiliary fiber insertion device according to claim 1, characterized in that, The front end of the optical fiber sheath fixing groove (4) is a plane perpendicular to the length direction of the optical fiber, which is used to abut against the front end of multiple optical fiber sheaths (6).

7. The aerospace fiber optic MT ferrule auxiliary fiber insertion device according to claim 1, characterized in that, The width of the optical fiber sheath fixing groove (4) is equal to the sum of the widths of the multiple optical fiber sheaths (6).

8. The aerospace fiber optic MT ferrule auxiliary fiber insertion device according to claim 1, characterized in that, When the clamping cover (1) is closed, the distance between the lower surface of the clamping cover (1) and the bottom of the optical fiber sheath fixing groove (4) is equal to the height of the optical fiber sheath (6). The lower surface of the clamping cover plate (1) forms a clamping part between the bottom of the optical fiber sheath fixing groove (4) and is used to clamp the optical fiber sheath (6).

9. The aerospace fiber optic MT ferrule auxiliary fiber insertion device according to claim 1, characterized in that, One side of the fiber sheath fixing groove (4) is connected to one side of the fiber cladding fixing groove (5), the other side of the fiber sheath fixing groove (4) extends to one side of the clamping base (2), and the other side of the fiber cladding fixing groove (5) extends to the other side of the clamping base (2).

10. The aerospace fiber optic MT ferrule auxiliary fiber insertion device according to claim 1, characterized in that, The length of the fiber cladding fixing groove (5) is no more than 7 mm.

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