Integrated control cable for aero-engine

Abstract

The utility model relates to a comprehensive control cable for an aero-engine, the outer end of an engine end cable is connected with an engine plug, the engine end cable comprises a fire-resistant lead, a temperature compensation lead, a single-core wire and a shielding wire, and the fire-resistant lead, the temperature compensation lead, the single-core wire and the shielding wire are integrally connected in a black aramid fiber sleeve in a penetrating manner; the plurality of engine end cables are respectively connected with a plurality of controller end cables through the wave-proof sleeve, the shielding wire comprises a low-frequency ignition signal wire and a plurality of high-frequency signal wires, the outer end of each controller end cable is connected with a controller plug, and the controller end cables are formed by connecting a fire-resistant wire, a temperature compensation wire, a single-core wire and a plurality of high-frequency signal wires in a black aramid fiber sleeve in a penetrating manner. According to various signal characteristic requirements, the wires are twisted and shielded, so that induced current can be quickly guided, electromagnetic interference of transmission signals is reduced, and the transmission performance of the cable is improved.

Description

Technical Field

[0001] The utility model relates to a cable, in particular to an aero-engine integrated control cable. Background Art

[0002] The control, detection signal transmission and power transmission between the digital electrical controller and the engine are usually connected by a variety of installation cables. A variety of cables are installed in the helicopter power cabin and crew cabin. Under long-term operation in harsh environments such as high temperature, humidity, and salt spray, the cable insulation layer will be aged rapidly, thus affecting the control, detection signal transmission and power transmission between the entire digital electrical control and the engine, making the digital electrical control unable to control normally. Summary of the invention

[0003] The utility model provides an aviation engine comprehensive control cable integrating environmental protection and electromagnetic protection.

[0004] The technical solution adopted by the utility model is: an integrated control cable for an aviation engine, characterized in that: it comprises a plurality of engine-end cables, a plurality of controller-end cables and an ignition signal line, the outer end of the engine-end cable is connected with an engine plug, the engine-end cable comprises a fire-resistant wire, a temperature-compensating wire, a single-core wire and a shielded wire, the fire-resistant wire, the temperature-compensating wire, the single-core wire and the shielded wire are integrated and connected in a black aramid sheath, a plurality of engine-end cables are respectively connected to a plurality of controller-end cables through a wave-proof sheath, the shielded wire comprises a low-frequency ignition signal line and a plurality of high-frequency signal lines, the outer end of the controller-end cable is connected with a controller plug, and the controller-end cable is connected with a fire-resistant wire, a temperature-compensating wire, a single-core wire and a plurality of high-frequency signal lines in a black aramid sheath.

[0005] The outer end of the cable at the engine end is sequentially attached to the engine plug through a heat shrink tube and the engine end tail.

[0006] The engine plug is a 83723 series plug, and the engine end attachment is a 83723 series plug attachment.

[0007] The outer end of the controller-side cable is sequentially connected to a controller plug through a corrugated tube and a controller end.

[0008] The controller plug is a J599 series plug, and the controller end is attached with a J599 series plug.

[0009] The fire-resistant conductor is coaxially composed of a copper alloy conductor, a wrapped calcined mica tape, a polyimide composite film, and a polytetrafluoroethylene layer from the inside to the outside.

[0010] The temperature compensation wire comprises a nickel-chromium conductor and a nickel-silicon conductor, both of which are compounded with an F4 insulating layer, and the nickel-chromium conductor and the nickel-silicon conductor are twisted and then sequentially compounded with a polyimide composite film, a nickel-plated copper wire shielding layer and a polytetrafluoroethylene layer.

[0011] The high-frequency signal line is a twisted pair or a triple twisted shielded line.

[0012] The twisted pair or triple twisted shielded wire comprises two or three silver-plated copper wire conductors, the outer surfaces of the silver-plated copper wire conductors are irradiated cross-linked X-ETFE and the outer surfaces are provided with nickel-plated copper wire shielding layers after twisting, and the outer surfaces of the nickel-plated copper wire shielding layers are provided with irradiated cross-linked X-ETFE.

[0013] The utility model integrates the ignition signal line, the engine end cable and the controller end cable into one, and the external sleeve is an integrated braided black aramid sleeve with a stable structure. The tail of each plug adopts a high-strength epoxy resin sealing structure to meet the requirements of vibration, impact and tensile strength. The cable adopts multiple strands of wire to enhance the flexibility of the cable and meet the requirements of anti-bending. The entire cable forms a force-bearing and sealed whole, and effectively resists environmental factors such as vibration, impact, rain, sand and dust, ensuring the working reliability of the product in any state. Combined with the use of the ignition signal line to send the ignition signal through the engine end plug, the fire-resistant wire transmits the parking signal, the single-core wire transmits the engine sensor signal, the single-core wire and shielded wire control the detection signal, and the temperature compensation wire outputs the temperature signal. According to the requirements of various signal characteristics, the wires are twisted and shielded, which can quickly guide the induced current, reduce the electromagnetic interference of the transmission signal, and improve the performance of the cable transmission. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the structure of the utility model;

[0015] Figure 2 This is a schematic diagram of the structure of the fire-resistant wire of the utility model;

[0016] Figure 3 This is a schematic diagram of the structure of the twisted pair shielded cable of the utility model;

[0017] Figure 4 This is a schematic diagram of the structure of the temperature compensation wire of the utility model.

[0018] In the figure: engine plug 1, heat shrink tube 2, engine end attachment 3, engine end cable 4, black aramid sleeve 5, ignition signal line 6, fire-resistant wire 7, temperature compensation wire 8, single core wire 9, twisted shielded pair wire 10, copper alloy wire 11, wrapped calcined mica tape 12, polyimide composite film 13, polytetrafluoroethylene layer 14, nickel-chromium conductor 15, nickel-silicon conductor 16, F4 insulation layer 17, nickel-plated copper wire shielding layer 18, silver-plated copper wire conductor 19, irradiated cross-linked X-ETFE20, controller end cable 21, corrugated tube 22, controller end attachment 23, controller plug 24, wave-proof sleeve 25. DETAILED DESCRIPTION

[0019] The following is a further description with reference to the accompanying drawings.

[0020] Figure 1-4 As shown, an aircraft engine integrated control cable includes an engine plug 1, a heat shrink tube 2, an engine end tail attachment 3, an engine end cable 4, a controller end cable 21, a corrugated tube 22, a controller end tail attachment 23, a controller plug 24, and a wave-proof sleeve 25.

[0021] The outer end of the engine-end cable 4 is connected to the engine plug 1 through the heat shrink tube 2 and the engine-end tail 3 in sequence. The engine-end cable includes an ignition signal line 6, a fire-resistant wire 7, a temperature compensation wire 8, a single core wire 9 and a twisted shielded pair 10. The ignition signal line 6, the fire-resistant wire 7, the temperature compensation wire 8, the single core wire 9 and the twisted shielded pair 10 are integrated and connected in the black aramid sleeve 5. Multiple engine-end cables 4 are connected to multiple controller-end cables 21 and ignition signal lines 6 through the wave-proof sleeve 25. The controller-end cable 21 is connected by a fire-resistant wire 7, a temperature compensation wire 8, a single core wire 9 and a twisted shielded pair 10 in a black aramid sleeve.

[0022] like Figure 2 The medium fire-resistant conductor 7 is coaxially composed of a copper alloy conductor 11, a wrapped calcined mica tape 12, a polyimide composite film 13, and a polytetrafluoroethylene layer 14 from the inside to the outside.

[0023] In this embodiment, the ignition signal line 6 is a low-frequency shielded line, such as Figure 3 The middle twisted pair shielded wire 10 comprises two silver-plated copper wire conductors 19, the outer periphery of the silver-plated copper wire conductors 19 is provided with radiation cross-linked X-ETFE 20 and after being twisted, an outer nickel-plated copper wire shielding layer 18 is provided, and the outer nickel-plated copper wire shielding layer 18 is provided with radiation cross-linked X-ETFE.

[0024] like Figure 4 The medium temperature compensation conductor 8 comprises a nickel-chromium conductor 15 and a nickel-silicon conductor 16, both of which are compounded with an F4 insulating layer 17, and the nickel-chromium conductor and the nickel-silicon conductor are twisted and then sequentially compounded with a polyimide composite film, a nickel-plated copper wire shielding layer and a polytetrafluoroethylene layer.

[0025] In this embodiment, the engine plug is preferably a 83723 series plug, and the engine end tail is preferably a 83723 series plug tail. The controller plug is preferably a J599 series plug, and the controller end tail is preferably a J599 series plug.

[0026] This embodiment is only for the transmission of ignition signal, parking signal, engine sensor signal, detection signal, temperature signal, on this basis, if there is any transmission of other signals, they can be transmitted through high-frequency signal lines.

Claims

1. An integrated control cable for aircraft engines, Features: It includes multiple engine-end cables, multiple controller-end cables and ignition signal wires. The outer end of the engine-end cable is connected to an engine plug. The engine-end cable includes a fire-resistant wire, a temperature-compensating wire, a single-core wire and a shielded wire. The fire-resistant wire, the temperature-compensating wire, the single-core wire and the shielded wire are integrated and inserted into a black aramid sheath. Multiple engine-end cables are respectively connected to multiple controller-end cables through a wave-proof sheath. The shielded wire includes a low-frequency ignition signal wire and multiple high-frequency signal wires. The outer end of the controller-end cable is connected to a controller plug. The controller-end cable is composed of a fire-resistant wire, a temperature-compensating wire, a single-core wire and multiple high-frequency signal wires inserted into a black aramid sheath.

2. An aircraft engine integrated control cable according to claim 1, Its characteristics are: The outer end of the cable at the engine end is sequentially attached to the engine plug through a heat shrink tube and the engine end tail.

3. An aircraft engine integrated control cable according to claim 2, Its characteristics are: The engine plug is a 83723 series plug, and the engine end attachment is a 83723 series plug attachment.

4. An aircraft engine integrated control cable according to claim 1, Its characteristics are: The outer end of the controller-side cable is sequentially connected to a controller plug through a corrugated tube and a controller end.

5. An aircraft engine integrated control cable according to claim 4, Its characteristics are: The controller plug is a J599 series plug, and the controller end is attached with a J599 series plug.

6. An aircraft engine integrated control cable according to claim 1, Its characteristics are: The fire-resistant conductor is coaxially composed of a copper alloy conductor, a wrapped calcined mica tape, a polyimide composite film, and a polytetrafluoroethylene layer from the inside to the outside.

7. An aircraft engine integrated control cable according to claim 1, Its characteristics are: The temperature compensation wire comprises a nickel-chromium conductor and a nickel-silicon conductor, both of which are compounded with an F4 insulating layer, and the nickel-chromium conductor and the nickel-silicon conductor are twisted and then sequentially compounded with a polyimide composite film, a nickel-plated copper wire shielding layer and a polytetrafluoroethylene layer.

8. An aircraft engine integrated control cable according to claim 1, Its characteristics are: The high-frequency signal line is a twisted pair or a triple twisted shielded line.

9. An aircraft engine integrated control cable according to claim 8, Its characteristics are: The twisted pair or triple twisted shielded wire comprises two or three silver-plated copper wire conductors, the outer surfaces of the silver-plated copper wire conductors are irradiated cross-linked X-ETFE and the outer surfaces of the nickel-plated copper wire shielding layer are arranged after twisting, and the outer surfaces of the nickel-plated copper wire shielding layer are irradiated cross-linked X-ETFE.

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