CN211319769U

CN211319769U - High-speed data transmission bus for aviation system equipment

Info

Publication number: CN211319769U
Application number: CN202020023938.6U
Authority: CN
Inventors: 汤代兵
Original assignee: Hubei Yuhong Photoelectric Industry Co ltd
Current assignee: Hubei Yuhong Photoelectric Industry Co ltd
Priority date: 2020-01-06
Filing date: 2020-01-06
Publication date: 2020-08-21
Anticipated expiration: 2030-01-06

Abstract

The utility model relates to a high-speed data transmission bus for aeronautical system equipment, including a plurality of insulation core, each insulation core's surface all winds the package and has the internal shield layer and winds the band, winds the package and has the internal shield layer, is in the same place and has interior sheath at surperficial crowded package around a plurality of insulation core parallels in band, interior sheath surface has external shield layer, outer jacket in proper order to wrap. The data transmission bus that this application adopted, the inner conductor is the silver-plated copper strand wires, signal transmission loss when having reduced the low frequency, the insulating layer adopts resistant high low temperature and the less micropore polytetrafluoroethylene film area of dielectric constant to wind the covering insulating, reduce cable external diameter and weight, signal transmission loss when reducing the high frequency reduces the capacitance value, promote transmission rate, design double-deck shielding structure promotes the signal line interference killing feature, the outer jacket uses and gathers perfluor ethylene propylene layer, improve the weatherability and the fire resistance of cable.

Description

High-speed data transmission bus for aviation system equipment

Technical Field

The utility model relates to a power cable technical field especially relates to aeronautical system equipment is with high-speed data transmission bus.

Background

With the rapid development of information technology, the operating speed of computers for aviation systems is continuously improved, the transmission rate of external connection equipment is higher and higher, electronic equipment has a new generation of data transmission bus interface, and the existing common high-speed data transmission connection cable is made of a normal-temperature material, so that the weather resistance is poor, the signal transmission loss is large, the electrical property is poor, the occupied space and weight are increased due to the large outer diameter of the product, and the requirements of related technical configuration of aviation equipment cannot be met.

SUMMERY OF THE UTILITY MODEL

In order to overcome prior art's the aforesaid not enough, the utility model provides an aeronautical system equipment is with high-speed data transmission bus, the weather resistance that solves the existence of current data transmission cable is poor, signal transmission is impaired, the interference killing feature is poor, product external diameter and weight are big etc. technical problem.

The utility model discloses a realize through following technical scheme:

high-speed data transmission bus for aeronautical system equipment, including a plurality of insulation core, each insulation core's surface all winds the package has the internal shield layer and winds the band, winds the package and has the internal shield layer, a plurality of insulation core parallel in the same place around the band and have interior sheath at the crowded package in surface, interior sheath surface cladding has outer shielding layer, outer jacket in proper order.

Furthermore, the insulated wire core comprises an inner conductor and an insulated layer coated outside the inner conductor, and the inner conductor is a plurality of silver-plated copper alloy stranded bodies.

Furthermore, a flow guide line is arranged between the inner conductor and the insulating layer, and the flow guide line adopts a plurality of silver-plated copper alloy stranded bodies.

Furthermore, four insulated wire cores are arranged, the inner shielding layer and the four insulated wire cores wound with the winding tape are arranged in a straight line, and the inner protective layer is extruded on the surface of the inner shielding layer.

Furthermore, the insulating layer adopts micropore polytetrafluoroethylene film tape insulating material, the insulating layer still crowded package has the outer cortex of fluorinated ethylene propylene outward.

Further, the inner shielding layer is a blue conductive aluminum foil layer.

Furthermore, the wrapping tape is a microporous polytetrafluoroethylene film tape.

Further, the inner protection layer adopts a fluorinated ethylene propylene layer.

Further, the outer shielding layer is made of a silver-plated copper alloy conductor with the density of more than 90%.

Furthermore, the outer protective layer adopts a fluorinated ethylene propylene layer.

Compared with the prior art, the beneficial effects of the utility model reside in that:

the utility model provides a high-speed data transmission bus is used to aeronautical system equipment, through using the good and high fire resistance of weatherability and the little micropore polytetrafluoroethylene film area of transmission loss as the signal transmission dielectric layer, form the shielding system reinforcing interference immunity that internal shield layer and external shield layer combined together on structural design. Meanwhile, the microporous polytetrafluoroethylene film belt with the oxygen index content of more than 95 is adopted, the flame retardance of the microporous polytetrafluoroethylene film belt is far superior to that of the traditional physical foaming polyethylene material, in addition, the microporous polytetrafluoroethylene film belt can work for a long time at the temperature of 100 ℃ below zero to 200 ℃, the transmission frequency of a high-speed data transmission bus for aviation system equipment can reach 6GHz, the transmission loss of a 24AWG silver-plated copper stranded conductor is not more than 0.6dB/m when the frequency is 0.6GHz, the transmission loss at the frequency of 1.25GHz is not more than 0.96dB/m, the near-end crosstalk attenuation is not less than 35dB at 6GHz, the differential impedance of the wire pair meets 100 +/-5 omega, the inner protective layer and the outer protective layer use fluorinated ethylene propylene material, the flame-retardant cable material has the characteristics of ageing resistance and corrosion resistance, and the flame-retardant performance of the flame-retardant cable material meets the grade A requirement of the combustion performance grade specified in the GB/T31247-2014 Cable and optical cable combustion performance grading standard.

Drawings

Fig. 1 is a structural diagram of a high-speed data transmission bus for an aircraft system device according to an embodiment of the present invention.

In the figure:

1. an inner conductor; 2. an insulating layer; 3. a diversion line; 4. an inner shield layer; 5. wrapping a tape; 6. an inner protective layer; 7. an outer shield layer; 8. an outer jacket; 9. an insulated wire core.

Detailed Description

The following examples are presented to illustrate certain embodiments of the invention and should not be construed as limiting the scope of the invention. The present disclosure may be modified from materials, methods, and reaction conditions at the same time, and all such modifications are intended to be within the spirit and scope of the present invention.

As shown in fig. 1, the high-speed data transmission bus for the aircraft system equipment comprises four insulated wire cores 9, an inner shielding layer 4 and a wrapping tape 5 are wrapped around the surface of each insulated wire core 9, the four insulated wire cores 9 wrapped with the inner shielding layer 4 and the wrapping tape 5 are parallel to form a straight line, an inner protection layer 6 is extruded on the surface of the four insulated wire cores, the inner protection layer extrusion of the four insulated wire cores is completed by adopting a synchronous production method, the original procedure of cabling the four insulated wire cores 9 and then extruding the inner protection layer is changed into the procedure of directly extruding the inner protection layer 6 from the four insulated wire cores 9 in parallel, the cabling procedure is reduced, and the cost is reduced; the surface of the inner protection layer 6 is sequentially coated with an outer shielding layer 7 and an outer protection layer 8.

In this embodiment, the insulated wire core 9 includes an inner conductor 1 and an insulating layer 2 coated outside the inner conductor 1, and the inner conductor 1 adopts a silver-plated copper alloy stranded body with a copper purity of 99.999% and a silver content of 10%, so as to reduce low-frequency signal transmission loss.

In this embodiment, a current guiding line 3 is further disposed between the inner conductor 1 and the insulating layer 2, and the current guiding line 3 adopts a plurality of silver-plated copper alloy stranded bodies to guide the interference source into the grounding body, so as to prevent mutual interference.

In this embodiment, insulating layer 2 adopts micropore polytetrafluoroethylene film tape insulating material, insulating layer 2 is outer still to crowded package has the outer cortex of fluorinated ethylene propylene, improves insulating weatherability and fire resistance.

In this embodiment, internal shield layer 4 adopts the blue face conductive aluminum foil layer that thickness is 70um, winds the package in insulating core 9 surface, and the contact of water conservancy diversion line 3 and the aluminium foil conducting surface in the insulating core 9 is favorable to welding to the terminal equipment above, will disturb the leading-in ground of electromagnetic clutter signal, reduces the mutual crosstalk between the signal.

In this embodiment, the wrapping tape 5 is made of a microporous polytetrafluoroethylene film tape and is wrapped on the surface of the inner shielding layer 4, and the material has excellent mechanical properties, transmission performance, environmental performance and safety performance.

In this embodiment, the inner sheath layer 6 is a layer of fluorinated ethylene propylene, which has the characteristics of high flame retardancy and corrosion resistance, and the fire resistance during combustion meets the requirements specified in class a (non-combustible cable) in the GB31247-2014 (cable and optical cable combustion performance classification) standard.

In this embodiment, the outer shielding layer 7 is made of a silver-plated copper alloy conductor with a density of 90% or more, and is coated on the surface of the inner sheath 6 in a 360-degree braided mesh manner, so that the electromagnetic compatibility of the cable is improved.

In this embodiment, outer jacket 8 adopts and gathers the perfluoroethylene propylene layer, gathers perfluoroethylene propylene layer 8 and possesses good weatherability, and the fire resistance can not produce dense smoke and other secondary harms when being burnt, can effectively ensure personnel's safety and property safety.

To sum up, adopt the data transmission bus of this application, can reduce low frequency transmission attenuation nature, the temperature resistance is good, does not receive ambient temperature to influence, reduces production processes, and the interference killing feature is strong, good electromagnetic compatibility, good weatherability and fire resistance.

The above only is the embodiment of the present invention, not limiting the patent scope of the present invention, all utilize the equivalent structure or equivalent flow transformation that the content of the specification does, or directly or indirectly use in other related technical fields, all including in the same way the patent protection scope of the present invention.

Claims

1. Aviation system is high-speed data transmission bus for equipment, its characterized in that, including a plurality of insulation core (9), each insulation core's (9) surface all has around internal shield layer (4) and around band (5), has around the band internal shield layer (4), a plurality of insulation core (9) parallel in the same place around band (5) and have interior sheath (6) at the crowded package in surface, interior sheath (6) surface cladding has outer shielding layer (7), outer jacket (8) in proper order.

2. The high-speed data transmission bus for the aeronautical system equipment according to claim 1, wherein the insulated wire core (9) comprises an inner conductor (1) and an insulating layer (2) coated outside the inner conductor (1), and the inner conductor (1) adopts a plurality of silver-plated copper alloy stranded bodies.

3. The high-speed data transmission bus for the aeronautical system equipment according to claim 2, wherein a guide line (3) is further arranged between the inner conductor (1) and the insulating layer (2), and the guide line (3) adopts a plurality of silver-plated copper alloy stranded bodies.

4. The high-speed data transmission bus for the aeronautical system equipment according to claim 1, wherein the number of the insulated wire cores (9) is four, and the four insulated wire cores (9) wrapped with the inner shielding layer (4) and the wrapping tape (5) are arranged in a straight line and are wrapped with the inner protective layer (6) in an extruded manner on the surface.

5. The high-speed data transmission bus for the aeronautical system equipment according to claim 2, wherein the insulating layer (2) is made of a microporous polytetrafluoroethylene film tape insulating material, and a fluorinated ethylene propylene outer skin layer is extruded outside the insulating layer (2).

6. The high-speed data transmission bus for aeronautical system equipment according to claim 1, wherein the inner shielding layer (4) is a blue-plane conductive aluminum foil layer.

7. The high-speed data transmission bus for the aeronautical system equipment according to claim 1, wherein the wrapping tape (5) is a microporous polytetrafluoroethylene film tape.

8. A high-speed data transmission bus for aeronautical system equipment according to claim 1, characterized in that the inner sheath (6) is a layer of fluorinated ethylene propylene.

9. A high-speed data transmission bus for aeronautical system equipment according to claim 1, wherein the outer shielding layer (7) is a silver-plated copper alloy conductor with a density of 90% or more.

10. The high-speed data transmission bus for aeronautical system equipment according to claim 1, characterized in that the outer sheath (8) is a layer of fluorinated ethylene propylene.