CN104155725B - Wall hermetically-sealed connector worn by high-air-tightness multicore multipath optical fiber - Google Patents
Wall hermetically-sealed connector worn by high-air-tightness multicore multipath optical fiber Download PDFInfo
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- CN104155725B CN104155725B CN201410419187.9A CN201410419187A CN104155725B CN 104155725 B CN104155725 B CN 104155725B CN 201410419187 A CN201410419187 A CN 201410419187A CN 104155725 B CN104155725 B CN 104155725B
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Abstract
The present invention discloses the junctor that wall sealing worn by a kind of high-air-tightness multicore multiple diameter optical fiber, comprise capsule shape housing, hollow seal sleeve pipe, enclosure interior sealing-ring, hollow screw bolt-type metallic briquette, and hull outside sealing-ring, capsule shape housing be located on spacecraft cabin wall or space environment simulation wall on and sealed by hull outside sealing-ring, capsule shape housing comprises first end hood, end hood and head and the tail connect fixing seal body interior with the two mutual spiral shells of hood respectively, the seal body interior of capsule shape housing is hollow structure, can pass side by side for diameter optical fiber more than many, the junctor of the present invention has high-air-tightness, component interchangeableness, physical construction is simple, low-loss, the advantages such as many diameter optical fiber are suitable for, solve high-air-tightness (the leakage rate < 1.0 �� 10 of the joints of optical fibre-7Pa L/S) low-loss multiple class many diameters multi-core fiber is tightly connected problem.
Description
Technical field
The invention belongs to spacecraft opticfiber communication linking device technical field, it is specifically related to a kind of wear wall hermetically-sealed connector for the high-air-tightness low-loss multicore multiple diameter optical fiber of the test of spacecraft ground space environmental simulation with spacecraft stage in orbit.
Background technology
Require to improve constantly along with China's spacecraft Project R&D, to temperature and the strain of measuring spacecraft under ground simulation space environment, Real-Time Monitoring spacecraft structure thermal distortion degree, material damage degree are very urgent with the demand carrying out heath state of spacecraft diagnosis in-orbit. Fibre-optical multiparameter composite sensing technology can meet large complicated satellite and large-sized structural parts (such as net-shape antenna, truss-frame structure, solar wing, mechanical arm etc.) the ground space envrionment test application demand with state of health diagnosis aspect in-orbit.
Spacecraft needs to complete vacuum thermal test in ground space environment simulator, and space environment simulator can the high vacuum thermal environment of simulation space. It is the big technical barrier that solution fibre-optical multiparameter composite sensing technology and Fibre Optical Communication Technology are applied under high vacuum environment that high-air-tightness multi-core fiber wears wall hermetically-sealed connector, and main purpose keeps the condition of high vacuum degree of space environment simulator inside (to be less than 1.0 �� 10 ensureing fiber-optic signal Lossless transport while-4Pa) with the vacuum tightness of spacecraft inside, the especially barometric point of manned space flight device and inside, space station.
Therefore, design and invention one can adapt to high vacuum and (be less than 1.0 �� 10-4Pa) the high-air-tightness low-loss multicore multiple diameter optical fiber of environment is worn wall hermetically-sealed connector and is had positive realistic meaning.
Summary of the invention
The technical problem to be solved in the present invention to be provided a kind of high-air-tightness low-loss multicore multiple diameter optical fiber that can adapt to high vacuum environment to wear wall hermetically-sealed connector, it is intended to keeps the condition of high vacuum degree of space environment simulator inside and the vacuum tightness of spacecraft inside while ensureing fiber-optic signal Lossless transport.
For solving the problems of the technologies described above, the technical solution used in the present invention is as follows:
Wall hermetically-sealed connector worn by high-air-tightness multicore multiple diameter optical fiber, comprise capsule shape housing, hollow seal sleeve pipe, enclosure interior sealing-ring, hollow screw bolt-type metallic briquette, and hull outside sealing-ring, capsule shape housing be located on spacecraft cabin wall or space environment simulation wall on and sealed by hull outside sealing-ring, capsule shape housing comprises first end hood, end hood and head and the tail connect fixing seal body interior with the two mutual spiral shells of hood respectively, the seal body interior of capsule shape housing is hollow structure, can pass side by side for diameter optical fiber more than many, in capsule shape enclosure interior, every root optical fiber is successively through hollow seal sleeve pipe, enclosure interior sealing-ring, installation trench bottom perforation on seal body interior side, by diameter optical fiber more than many side by side through hollow seal sleeve pipe, filling adhesive seal material in hollow seal sleeve pipe, form resistance to air loss optical fiber seal sleeve pipe, by hollow seal sleeve pipe, the installation cavity that the installation groove of seal body interior is arranged put into by enclosure interior sealing-ring, and be fixed, the tail end of all optical fiber is through hollow screw bolt-type metallic briquette, metallic briquette is put into through hollow seal sleeve pipe and is installed cavity, it is placed in the top end face of enclosure interior sealing-ring, extruding metallic briquette is rotated by instrument, compression inner seal rings, complete the hermetic seal of hollow seal sleeve pipe and seal body interior, it is achieved the sealing of seal connector shell inside, cabin worn by optical fiber.
Wherein, in the installation groove of seal body interior, it is provided with the installation cavity of anti-convex shape, hollow seal sleeve pipe, enclosure interior sealing-ring is put into and cavity is installed and is fixed.
Wherein, the diameter of hollow seal sleeve pipe is less than the diameter of enclosure interior sealing-ring and installs the diameter of cavity bottom perforated, hollow seal sleeve pipe installs cavity bottom perforated through enclosure interior sealing-ring and seal body interior, the diameter of enclosure interior sealing-ring is less than the diameter that seal body interior installs cavity, it is greater than the diameter installing cavity bottom perforated, so that it is fastened on the inwall installing cavity.
Wherein, the diameter of hollow seal sleeve pipe is less than hollow screw bolt-type metallic briquette diameter, metallic briquette is put into enclosure interior through hollow seal sleeve pipe and is installed cavity, it is placed in end face above enclosure interior sealing-ring, extruded hollow screw bolt-type metallic briquette is rotated by instrument, compression inner seal rings, completes the hermetic seal of Sealed casing pipe and seal body interior.
Wherein, capsule shape housing, by nut, is mechanically fixed on the body wall flange of cabin.
Wherein, hood sidewall being provided with hollow out viewing window, for observing, the fastening form of enclosure interior optical fiber prevents bending between cable line winding to described hollow out viewing window.
Wherein, the outside of first end hood, end hood arranges outstanding head end lockout mechanism and tail end lockout mechanism respectively to fix optical cable head end and optical cable tail end respectively.
The advantages such as the junctor of the present invention has that high-air-tightness, component interchangeableness, physical construction are simple, low-loss, many diameter optical fiber are suitable for, solve high-air-tightness (the leakage rate < 1.0 �� 10 of the joints of optical fibre-7Pa L/S) low-loss multiple class many diameters multi-core fiber is tightly connected technical barrier. Utilizing this junctor can realize only optical fiber sensing system is positioned in container without electrical part (Fibre Optical Sensor and Transmission Fibers), electrification device is positioned over outside container, from internal tank condition of high vacuum degree and very low temperature (temperature <-190 DEG C) environmental influence. This junctor size adaptive space environment simulator wall approach blue electricity interface size, device exchanges with being electrically connected can to realize the joints of optical fibre, without the need to making separately simulator wall approach orchid for the joints of optical fibre, realize the nuclear interface standardizing of test specimen upper sensor end to simulator infrared optical fiber link, do not damage insertion loss and the return loss spectrophotometric data of optical fiber, realize the Lossless transport of optical signalling, stable mechanical performance, and, these joints of optical fibre also can apply the spacecraft stage in orbit, ensures spacecraft inner vacuum degree while both having ensured fiber-optic signal Lossless transport.
Accompanying drawing explanation
Fig. 1 illustrates that wall seal connector shell assembly schematic perspective view worn by the high-air-tightness low-loss multicore multiple diameter optical fiber according to one exemplary embodiment of the present invention, and wherein first end hood 100, end hood 300 are in the state being separated with seal body interior 200. Wherein, 10 is afterbody lockout mechanism for head end lockout mechanism, 11,31 is hollow out viewing window, 30;
Fig. 2 illustrates that the high-air-tightness low-loss multicore multiple diameter optical fiber according to one exemplary embodiment of the present invention wears wall hermetically-sealed connector seal body interior 200, hollow seal sleeve pipe 22, enclosure interior sealing-ring 23, hollow screw bolt-type metallic briquette 21 assembly schematic perspective view, and wherein seal body interior 200, hollow seal sleeve pipe 22, enclosure interior sealing-ring 23, hollow screw bolt-type metallic briquette 21 are in the state of connection. Wherein, 24 is positioning screw hole, 26, install trench bottom perforation;
Fig. 3 is another view stereo schematic diagram of Fig. 2.
Wherein, 25, hull outside sealing-ring.
Fig. 4 is the seal body interior schematic perspective view illustrated shown in Fig. 2.
Wherein, 27, cavity is installed.
Embodiment
Referring to accompanying drawing, the structure that wall hermetically-sealed connector worn by the high-air-tightness low-loss multicore multiple diameter optical fiber of the present invention is described in detail, but this description is only exemplary, is not intended to protection scope of the present invention is carried out any restriction.
As shown in Figure 1 to Figure 3, wall hermetically-sealed connector worn by high-air-tightness low-loss multicore multiple diameter optical fiber, comprise capsule shape housing, hollow seal sleeve pipe 22, enclosure interior sealing-ring 23, hollow screw bolt-type metallic briquette 21, and hull outside sealing-ring 25, capsule shape housing be located on spacecraft cabin wall or space environment simulation wall on and sealed by hull outside sealing-ring 25, capsule shape housing comprises first end hood 100, end hood 300 and head and the tail connect fixing seal body interior 200 with the two mutual spiral shells of hood respectively, the seal body interior 200 of capsule shape housing is hollow structure, can pass side by side for diameter optical fiber more than many, in capsule shape enclosure interior, every root optical fiber is successively through hollow seal sleeve pipe 22, enclosure interior sealing-ring 23, installation trench bottom perforation on seal body interior 200 side, by diameter optical fiber more than many side by side through hollow seal sleeve pipe 22, filling adhesive seal material in hollow seal sleeve pipe 22, form resistance to air loss optical fiber seal sleeve pipe, by hollow seal sleeve pipe 22, the installation cavity 27 that the installation groove of seal body interior 200 is arranged put into by enclosure interior sealing-ring 23, and be fixed, the tail end of all optical fiber is through hollow screw bolt-type metallic briquette, metallic briquette is put into through hollow seal sleeve pipe and is installed cavity 27, it is placed in the top end face of enclosure interior sealing-ring, extruding metallic briquette is rotated by instrument, compression inner seal rings, complete the hermetic seal of hollow seal sleeve pipe 22 with seal body interior 200, it is achieved the sealing of seal connector shell inside, cabin worn by optical fiber.
In a concrete enforcement mode, as shown in Figure 1, it is preferable that the head end lockout mechanism 10 given prominence in the first end hood 100 of capsule shape housing, the outer setting of end hood 300 fixes optical cable head end, and outstanding afterbody lockout mechanism 30 fixes optical cable tail end. In fixation procedure, it is preferable that housing head end can be observed by the hollow out viewing window 11 and 31 of the lockout mechanism both sides shown in Fig. 1 and the fastening form of tail end internal optical fiber prevents bending between cable winding, avoid fibre-optical bending curvature and the bending loss of signal caused,
Fig. 2 illustrates that the high-air-tightness low-loss multicore multiple diameter optical fiber according to one exemplary embodiment of the present invention wears wall hermetically-sealed connector seal body interior 200, hollow seal sleeve pipe 22, enclosure interior sealing-ring 23, hollow screw bolt-type metallic briquette 21 assembly schematic perspective view, and wherein seal body interior 200, hollow seal sleeve pipe 22, enclosure interior sealing-ring 23, hollow screw bolt-type metallic briquette 21 are in the state of connection. Wherein the every root optical fiber of cable interior is successively through hollow seal sleeve pipe 22, enclosure interior sealing-ring 23, seal body interior installs trench bottom perforation 26 (see Fig. 1), by diameter optical fiber more than many side by side through hollow seal sleeve pipe 22, in hollow seal pipe filling adhesive seal material, formed resistance to air loss optical fiber seal sleeve pipe. Then, hollow seal sleeve pipe 22, enclosure interior sealing-ring 23, successively through the seal body interior 200 of enclosure interior sealing-ring 23 and capsule shape housing, are put into the installation cavity 27 of seal body interior 200 and are fixed by optical fiber.
The tail end of all optical fiber is through hollow screw bolt-type metallic briquette 21, metallic briquette 21 is put into enclosure interior through hollow seal sleeve pipe 22 and is installed cavity 27, it is placed in the top end face of enclosure interior sealing-ring 23, extruded hollow screw bolt-type metallic briquette 21 is rotated by instrument, compression inner seal rings 23, complete the hermetic seal of Sealed casing pipe 22 with seal body interior 200, it is achieved the sealing of seal connector shell inside, cabin worn by optical fiber.
Then, by optical fiber through first end hood 100, end hood 300, it is that wall hermetically-sealed connector worn by high-air-tightness low-loss multicore multiple diameter optical fiber by optical fiber and capsule shape shell combination.
Finally by optical cable through wall flange, positioning screw hole 24 shown in connector shell nut and Fig. 2 is fixed on flange, realizes, by hull outside sealing-ring 25 (see Fig. 3), the cabin body wall flange that optical fiber wears between cabin seal connector shell and spacecraft cabin and seal.
In an embodiment, in the installation groove of seal body interior 200, it is provided with the installation cavity 27 (see Fig. 3) of anti-convex shape, hollow seal sleeve pipe 22, enclosure interior sealing-ring 23 is put into and cavity 27 is installed and is fixed. The diameter of hollow seal sleeve pipe 22 is less than the diameter of enclosure interior sealing-ring 23 and installs the diameter of cavity 27 bottom perforated, hollow seal sleeve pipe 22 installs cavity 27 bottom perforated through enclosure interior sealing-ring 23 and seal body interior, the diameter of enclosure interior sealing-ring 23 is less than the diameter that seal body interior installs cavity 27, it is greater than the diameter installing cavity 27 bottom perforated, so that it is fastened on the inwall installing cavity 27.
Preferably, the diameter of hollow seal sleeve pipe 22 is less than hollow screw bolt-type metallic briquette 21 diameter, metallic briquette 21 is put into enclosure interior through hollow seal sleeve pipe and is installed cavity 27, it is placed in end face above enclosure interior sealing-ring 23, extruded hollow screw bolt-type metallic briquette 21 is rotated by instrument, compression inner seal rings 23, completes the hermetic seal of Sealed casing pipe and seal body interior.
The invention solves the high-air-tightness of the joints of optical fibre (leakage rate < 1.0 �� 10-7Pa L/S) be tightly connected technical barrier, achieve optical fiber sensing system electrical part be positioned over external container cannot normal operation from internal tank condition of high vacuum degree and very low temperature (temperature <-190 DEG C) environmental influence, only it is positioned over internal tank without electrical part (Fibre Optical Sensor and Transmission Fibers), and this junctor can be operated in vacuum (< 1.0 �� 10-4Pa) thermal environment (-200 DEG C��200 DEG C), use in multiple model vacuum thermal test, result shows: these joints of optical fibre achieve and keep the condition of high vacuum degree of space environment simulator inside and the vacuum tightness of spacecraft inside while ensureing fiber-optic signal Lossless transport, and stable mechanical performance, ensure spacecraft ground Optical Fiber Force Thermal test comprehensive test 24 hours continuous reliability services, meet model demand.
Describe in detail and explanation although above the specific embodiment of the present invention being given; but what should indicate is; above-mentioned enforcement mode can be carried out various equivalence according to the conception of the present invention and change and amendment by us; its function produced does not exceed specification sheets yet and accompanying drawing is contained spiritual time, all should within protection scope of the present invention.
Claims (6)
1. the junctor of wall sealing worn by high-air-tightness multicore multiple diameter optical fiber, comprise capsule shape housing, hollow seal sleeve pipe, enclosure interior sealing-ring, hollow screw bolt-type metallic briquette, and hull outside sealing-ring, capsule shape housing be located on spacecraft cabin wall or space environment simulation wall on and sealed by hull outside sealing-ring, capsule shape housing comprises first end hood, end hood and head and the tail connect fixing seal body interior with the two mutual spiral shells of hood respectively, the seal body interior of capsule shape housing is hollow structure, can pass side by side for diameter optical fiber more than many, in capsule shape enclosure interior, every root optical fiber is successively through hollow seal sleeve pipe, enclosure interior sealing-ring, wherein, installation trench bottom on seal body interior side arranges perforation, diameter optical fiber more than many to be passed side by side hollow seal sleeve pipe, filling adhesive seal material in hollow seal sleeve pipe, form resistance to air loss optical fiber seal sleeve pipe, hollow seal sleeve pipe, enclosure interior sealing-ring are put into the installation cavity that the installation groove of seal body interior is arranged, and be fixed, the tail end of all optical fiber is through hollow screw bolt-type metallic briquette, metallic briquette is put into through hollow seal sleeve pipe and is installed cavity, it is placed in the top end face of enclosure interior sealing-ring, extruding metallic briquette is rotated by instrument, compression inner seal rings, complete the hermetic seal of hollow seal sleeve pipe and seal body interior, it is achieved the sealing of seal connector shell inside, cabin worn by optical fiber, capsule shape housing, by nut, is mechanically fixed on the body wall flange of cabin.
2. junctor as claimed in claim 1, wherein, is provided with the installation cavity of anti-convex shape in the installation groove of seal body interior, hollow seal sleeve pipe, enclosure interior sealing-ring is put into and installs cavity and be fixed.
3. junctor as claimed in claim 1, wherein, the diameter of hollow seal sleeve pipe is less than the diameter of enclosure interior sealing-ring and installs the diameter of cavity bottom perforated, hollow seal sleeve pipe installs cavity bottom perforated through enclosure interior sealing-ring and seal body interior, the diameter of enclosure interior sealing-ring is less than the diameter that seal body interior installs cavity, it is greater than the diameter installing cavity bottom perforated, so that it is fastened on the inwall installing cavity.
4. junctor as claimed in claim 3, wherein, the diameter of hollow seal sleeve pipe is less than hollow screw bolt-type metallic briquette diameter, metallic briquette is put into enclosure interior through hollow seal sleeve pipe and is installed cavity, it is placed in end face above enclosure interior sealing-ring, rotating extruded hollow screw bolt-type metallic briquette by instrument, compression inner seal rings, completes the hermetic seal of Sealed casing pipe and seal body interior.
5. junctor as described in item as arbitrary in claim 1-4, wherein, hood sidewall is provided with hollow out viewing window, and for observing, the fastening form of enclosure interior optical fiber prevents bending between cable line winding to described hollow out viewing window.
6. junctor as described in item as arbitrary in claim 1-4, wherein, the outside of first end hood, end hood arranges outstanding head end lockout mechanism and tail end lockout mechanism respectively to fix optical cable head end and optical cable tail end respectively.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410419187.9A CN104155725B (en) | 2014-08-22 | 2014-08-22 | Wall hermetically-sealed connector worn by high-air-tightness multicore multipath optical fiber |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410419187.9A CN104155725B (en) | 2014-08-22 | 2014-08-22 | Wall hermetically-sealed connector worn by high-air-tightness multicore multipath optical fiber |
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| CN104155725B true CN104155725B (en) | 2016-06-08 |
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| CN106641467A (en) * | 2016-09-22 | 2017-05-10 | 北京空间飞行器总体设计部 | High-heat-resistance sealed cabin pipeline cabin penetration flange and machining method |
| CN106353856A (en) * | 2016-09-30 | 2017-01-25 | 华东理工大学 | Vacuum bare fiber introducing device |
| CN107678102A (en) * | 2017-11-16 | 2018-02-09 | 广州市光机电技术研究院 | A kind of optical fiber splicing device for coordinating vacuum equipment to use and method |
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| US20070249193A1 (en) * | 2006-04-04 | 2007-10-25 | Applied Optical Systems, Inc. | Universal hybrid electrical/fiber optic insert cap and hybrid connector and methods |
| US8792759B2 (en) * | 2011-04-11 | 2014-07-29 | Advanced Fiber Products, LLC | Gigabit wet mate active cable |
| CN203069832U (en) * | 2012-12-13 | 2013-07-17 | 奉化市宇达高科光电器件有限公司 | Single-connection integrated adapter |
| CN103018847B (en) * | 2012-12-26 | 2015-01-14 | 中国航天时代电子公司 | Optical fiber cabin-penetrating sealing connection socket device used for sealing cabin |
| CN203133326U (en) * | 2013-02-08 | 2013-08-14 | 中国电子科技集团公司第八研究所 | Watertight connector for guide optical cable |
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Inventor after: Zhang Jingchuan Inventor after: Yang Xiaoning Inventor after: Xie Jihui Inventor after: Pei Yifei Inventor after: Qian Beixing Inventor after: Zhang Lina Inventor after: Guan Laishui Inventor after: Tian Yuan Inventor after: Zhong Jianwei Inventor before: Qian Beixing Inventor before: Zhang Jingchuan Inventor before: Xie Jihui Inventor before: Zhang Lina Inventor before: Guan Laishui Inventor before: Pei Yifei Inventor before: Tian Yuan Inventor before: Zhong Jianwei |