A multi-line suspension system cable arrangement

Abstract

The application provides a multi-line suspension system cable device, which comprises a rectangular connector, a data bus coupler and a power divider, an aircraft end electrical docking mechanism, a suspended object end electrical docking mechanism, a pull-off electrical connector and an electrical connector, the input end of the rectangular connector is connected with the aircraft end electrical docking mechanism, the first output end of the rectangular connector is connected with the pull-off electrical connector through the data bus coupler and the power divider, the second output end of the rectangular connector is connected with the suspended object end electrical docking mechanism through the data bus coupler and the power divider, and the third output end of the rectangular connector is connected with the electrical connector. The electrical docking mechanism is used for realizing the docking between the electrical connectors, providing a feedback signal to keep locking and guaranteeing the reliability of transmission; the rectangular connector guarantees the reliable transmission of electrical signals and air path pressure, and improves the modular integration degree; the data bus coupler and the power divider are used for branching, so that the wiring is reduced and the utilization rate of the electrical connector hole group is improved.

Description

TECHNICAL FIELD

[0001] The present specification relates to the technical field of suspension system cables, in particular to a multi-line suspension system cable device. BACKGROUND

[0002] With the continuous upgrading of main battle models, the technical and tactical indicators of weapon equipment systems are also improved, and the number of ammunition hung by the weapon suspension device is increasing, and the installation space on the aircraft is compressed. The traditional structure wire harness cannot realize the functions of low-frequency, high-frequency, bus, air path and other signal transmission at the same time. At the same time, affected by the internal space of the suspension device, too many single transmission form wire harnesses will interfere with each other when laid in the suspension device, and even cannot be installed. At the same time, the traditional electrical connector is prevented from loosening by a fuse after being connected with the aircraft end, and at present, with the increase of the vibration level of artillery fire and the compression of the weapon compartment space, the traditional method of beating the fuse to prevent loosening cannot meet the system requirements. SUMMARY

[0003] Therefore, the embodiments of the present specification provide a multi-line suspension system cable device to achieve the functions of ensuring the electrical connector to be connected, retained and locked, and to ensure the reliable transmission of electrical signals between the carrier aircraft and the launching device.

[0004] The embodiments of the present specification provide the following technical solutions:

[0005] A multi-line suspension system cable device comprises:

[0006] A rectangular connector, a data bus coupler and a power divider, an aircraft end electrical connection mechanism, a suspended object end electrical connection mechanism, a pull-off electrical connector and an electrical connector, the rectangular electrical connector is fixed on the aircraft end electrical connection mechanism, the input end of the rectangular connector is connected with the aircraft end electrical connection mechanism, the first output end of the rectangular connector is connected to the pull-off electrical connector through the data bus coupler and the power divider, the second output end of the rectangular connector is connected to the suspended object end electrical connection mechanism through the data bus coupler and the power divider, and the third output end of the rectangular connector is connected with the electrical connector.

[0007] Further, the rectangular connector comprises:

[0008] A low-frequency cavity, the low-frequency signal branch of the low-frequency cavity is connected to the pull-off electrical connector or the electrical connector or the electrical connector on the suspended object end electrical connection mechanism;

[0009] A high-frequency cavity, the high-frequency signal of the high-frequency cavity is connected to the pull-off electrical connector or the electrical connector on the suspended object end electrical connection mechanism after being branched through the data bus coupler and the power divider;

[0010] An air path channel and a pipe connecting piece, the air path pressure is transmitted to the external suspension device through the air path channel and the pipe connecting piece.

[0011] Further, the rectangular connector further comprises a conduit locking assembly, and the rectangular connector is locked with the rectangular electrical connector of the external suspension device through the locking assembly.

[0012] Further, the data bus coupler and the power divider comprise:

[0013] The data bus coupler comprises a coupler input end and a plurality of coupler output ends, the coupler input end is connected with the rectangular connector, the first coupler output end is connected with the pull-off electrical connector, and the second coupler output end is connected with the suspension end electrical docking mechanism.

[0014] The power divider comprises an input end SMA radio frequency plug and a plurality of output end SMA radio frequency plugs, the input end SMA radio frequency plug is connected with the rectangular connector, the first output end SMA radio frequency plug is connected with the pull-off electrical connector, and the second output end SMA radio frequency plug is connected with the suspension end electrical docking mechanism.

[0015] Further, the data bus coupler is a SYMB / A type twin wire data bus coupler.

[0016] Further, the power divider is an HDDS2SMAK-3 power divider.

[0017] Further, the multi-line suspension system cable device further comprises a wave-proof sleeve, the wave-proof sleeve is sleeved outside the wires between the data bus coupler and the power divider and the aircraft end electrical docking mechanism, the wires between the data bus coupler and the power divider and the electrical suspension end electrical docking mechanism, the wires between the data bus coupler and the power divider and the electrical connector, and the wires between the data bus coupler and the power divider and the pull-off electrical connector.

[0018] Further, the aircraft end electrical docking mechanism comprises:

[0019] The driving block is rotatably arranged at both ends of the aircraft end electrical docking mechanism, and the rectangular connector of the suspension device and the rectangular connector of the aircraft end are docked through the driving block.

[0020] The micro switch is used for feeding back whether the electrical connection is achieved or not.

[0021] The screw mounting hole is used for fixing the aircraft end electrical docking mechanism on the suspension device.

[0022] Further, the multi-line suspension system cable device further comprises a fixing clamp, and the data bus coupler and the power divider are fixed on the launching device through the fixing clamp.

[0023] Compared with the prior art, the at least one technical solution adopted by the embodiment of the present specification can achieve the beneficial effects at least including:

[0024] The multi-line suspension system cable device of the embodiment of the present application realizes the butt joint between the electrical connectors through the electrical butt joint mechanism, provides butt joint in place feedback signals, and provides a certain locking holding force, ensuring the reliability of signal transmission of the electrical connection in the high gun shock vibration environment; the rectangular connector can ensure the reliable transmission of electrical signals and air path pressure, and improve the modularization and integration level of the multi-line suspension system cable device; the data bus coupler and the power divider are used to branch the signals, and the signals are synchronously transmitted to the suspended object, reducing the wiring, improving the utilization rate of the electrical connector hole group in the limited space, and realizing more functions. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0026] Figure 1 is the overall structure diagram of the multi-line suspension system cable device of the embodiment of the present application;

[0027] Figure 2 is the schematic diagram of the electrical butt joint mechanism of the embodiment of the present application;

[0028] Figure 3 is the schematic diagram of the rectangular connector structure of the embodiment of the present application;

[0029] Figure 4 is the schematic diagram of the data bus coupler structure of the embodiment of the present application;

[0030] Figure 5 is the schematic diagram of the power divider structure of the embodiment of the present application;

[0031] Figure 6 is the schematic diagram of the fixed clamp structure of the embodiment of the present application.

[0032] Explanation of reference signs: 1, pull-off electrical connector; 2, electrical mating mechanism at the aircraft end; 201, driving block; 202, micro switch; 203, spring; 204, screw mounting hole; 205, rectangular electrical connector at the aircraft end; 206, rectangular electrical connector of the external suspension device; 3, electrical connector; 4, data bus coupler and power divider; 401, data bus coupler; 4011, coupler input end; 4012, coupler output end; 402, power divider; 4021, input end SMA radio frequency plug; 4022, output end SMA radio frequency plug; 5, wave protection sleeve; 6, rectangular connector; 601, low frequency cavity; 602, air path channel; 603, high frequency cavity; 604, locking assembly; 605, catheter connecting piece; 7, electrical mating mechanism at the suspension end; 8, fixed clamp. DETAILED DESCRIPTION

[0033] The embodiments of the present application will be described below in detail with reference to the drawings.

[0034] The embodiments of the present application will be described below in detail with reference to the drawings.

[0035] It is to be understood that the ranges and amounts of the ingredients described herein are approximations. Unless otherwise indicated, the amounts can vary. Also, the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting. It is also possible in the art to use other chemistries and techniques for the same or similar purpose. It is intended that each of the limitations as set forth in the claims below are fully supported by this disclosure.

[0036] It is also need to be explained that the figures provided in the following embodiments only schematically illustrate the basic ideas of the present application, and only the components related to the present application are shown in the figures, not the number, shape and size of the components when actually implemented, and the shape, number and ratio of the components when actually implemented can be arbitrarily changed, and the component layout pattern can also be more complex.

[0037] In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, one skilled in the art will understand that the described aspects can be practiced without these specific details.

[0038] The multi-line cable device of the embodiment of the present application mainly provides the functions of electric connector docking, locking of the rectangular electric connector 205 at the aircraft end and the rectangular electric connector 206 of the external suspension device, and ensures the reliable transmission of electrical signals between the aircraft and the external suspension device.

[0039] The technical solutions provided by the embodiments of the present application are described below with reference to the accompanying drawings.

[0040] Reference Figure 1 The multi-line cable device of the embodiment of the present application comprises a pull-off electric connector 1, an aircraft end electrical docking mechanism 2, a suspension end electrical docking mechanism 7, a rectangular connector 6, an electric connector 3, a data bus coupler and power divider 4, a wave-proof sleeve 5 and a fixing clamp 8. The rectangular connector 6 is fixed on the aircraft end electrical docking mechanism 2, the input end of the rectangular connector 6 is connected to the aircraft end electrical docking mechanism 2, the first output end of the rectangular connector 6 is connected to the pull-off electric connector 1 through the data bus coupler and power divider 4, the second output end of the rectangular connector 6 is connected to the suspension end electrical docking mechanism 7 through the data bus coupler and power divider 4, and the third output end of the rectangular connector 6 is connected to the electric connector 3.

[0041] In view of the limited space after the suspension device is installed in the aircraft weapon compartment, it is difficult to install manually, and in order to facilitate the inspection work after replacing the suspended ammunition and improve the maintainability of the product, the aircraft end electrical docking mechanism 2 is designed to realize quick docking. The aircraft end electrical docking mechanism 2 provides a docking in-place feedback signal (transmits the docking in-place signal to the cockpit) and provides a certain locking holding force, which ensures the reliability of signal transmission of the electrical connection in a high gun vibration environment. The aircraft end electrical docking mechanism 2 can replace the anti-loose locking mode of the traditional connector (such as locking, lead sealing, thread glue, etc.), and the aircraft end electrical docking mechanism 2 provides the locking function in the separated state and the locking function in the docking in-place state at the same time through the spring according to the use environment conditions.

[0042] The data bus coupler and power divider 4 are fixed on the launching device through the fixing clamp 8.

[0043] AsFigure 2 As shown, in order to butt joint and lock the rectangular plug at the suspension end with the rectangular socket at the aircraft end in a narrow space, the multi-line cable device of the embodiment of the application selects the aircraft end electrical butt joint mechanism 2 to realize the butt joint between the electrical connectors.

[0044] The aircraft end electrical butt joint mechanism 2 comprises a driving block 201, a micro switch 202, a spring 203, a screw mounting hole 204, a rectangular electrical connector 205 at the aircraft end and a rectangular electrical connector 206 of the external suspension device. The rectangular electrical connector 205 at the aircraft end is an electrical connector provided at the aircraft end, and the rectangular electrical connector 206 of the external suspension device is an electrical connector provided at the external suspension device. The driving block 201 is rotatably arranged at both ends of the aircraft end electrical butt joint mechanism 2, and the rectangular electrical connector 206 of the external suspension device and the rectangular electrical connector 205 at the aircraft end are butt jointed through the driving block 201. The aircraft end electrical butt joint mechanism 2 is fixed on the suspension device through the screw mounting hole 204 and a screw, and has a separation state locking function and a butt joint in place locking function. By rotating the driving block 201 with a hexagonal wrench, the rectangular plug at the suspension end is butt jointed with the rectangular socket at the aircraft end. After butt jointing in place, the mounting plate of the rectangular socket at the aircraft end triggers the micro switch 202 at one side of the electrical butt joint mechanism, thereby turning on the circuit and providing a butt joint in place feedback signal. After butt jointing, the spring 203 provides a butt joint state retaining force, thereby ensuring the reliability of signal transmission of the electrical connection in a high-velocity gun shock vibration environment. In the separation state, the spring also provides a separation state retaining force, thereby enabling the plug at the suspension end to maintain a stable state in a non-working environment.

[0045] As shown, Figure 3 The rectangular connector 6 of the multi-line transmission channel of the multi-line suspension system cable device of the embodiment of the application comprises a high-frequency cavity 603, a low-frequency cavity 601, an air path channel 602, a locking assembly 604 and a conduit connecting piece 605, and can ensure the reliable transmission of electrical signals and air path pressure. In order to meet the functional expansion of the user on the suspension device and improve the modularization and integration degree, the design is made in accordance with GJB 1188A “Interface Requirements for Aircraft / Suspension Electrical Connection System”. In order to avoid crosstalk between the high-frequency line and the low-frequency line, separate high-frequency cavities 603 and low-frequency cavities 601 are used for arrangement. The suspension at the customer suspension device is locked and unlocked through the air path. In order to meet the air path connection between the aircraft end and the suspension device end, the air path channel 602 is added in the middle of the rectangular connector 6, which is used to provide an air path connection meeting the air pressure requirements of the user. The rectangular connector 6 is locked with the rectangular electrical connector 206 of the external suspension device through the locking assembly 604. The air path pressure is transmitted to the external suspension device through the air path channel 602 and the conduit connecting piece 605.

[0046] The data bus coupler and power divider 4 includes a data bus coupler 401 and a power divider 402 which are independently arranged. As shown in Figure 5 The data bus coupler 401 includes a coupler input end 4011 connected to the rectangular electrical connector 206 of the external suspension device and a plurality of coupler output ends 4012 connected to the pull-off electrical connector 1 and the suspension end electrical docking mechanism 7 respectively. As shown in Figure 6 The power divider 402 includes a power divider body, an input end SMA radio frequency plug 4021 connected to the rectangular electrical connector 206 of the external suspension device and a plurality of output end SMA radio frequency plugs 4022 connected to the pull-off electrical connector 1 and the suspension end electrical docking mechanism 7 respectively. The data bus coupler and the power divider are used to respectively divide the 1553B data bus signal and the high-bandwidth radio frequency signal, transmit the signals to the suspension, reduce the wiring, improve the utilization rate of the connector hole group in the limited space, and realize more functions.

[0047] In some embodiments, in order to reliably and effectively transmit the 1553B data bus signal to the suspension, the multi-line suspension system cable device uses a SYMB / A type twin-line data bus coupler to divide the bus signal.

[0048] In some embodiments, when one end of the rectangular connector 6 needs to suspend a plurality of air-to-ground missiles and the other end of the rectangular connector 6 needs to suspend a plurality of air-to-air missiles, due to the particularity of the structure of the suspension device, it is necessary to reduce the wiring at the suspension device end. Therefore, the data bus coupler and the power divider 4 are used to respectively divide the 1553B data bus signal and the high-bandwidth radio frequency signal, and the low-frequency signal is divided by a dead joint. The control signal at the aircraft end can be used for left air-to-ground missile launching function and right air-to-air missile launching function on one set of wiring.

[0049] In some embodiments, the power divider 402 uses a HDDS2 SMA K-3 power divider.

[0050] In some embodiments, in order to fully utilize the space of the suspension device, the data bus coupler 401 and the power divider 402 are arranged in a concentrated manner using a glass cloth tape, and are then protected by winding an insulating self-adhesive tape to prevent abrasion and reduce insulation performance. In order to further prevent the data bus coupler 401 and the power divider 402 from being affected by electromagnetic interference, a BLDDY-1-L conductive cloth is tightly wound outside the data bus coupler 401 and the power divider 402, and is continuously connected with the outermost wave-proof sleeve of the multi-line suspension system cable device. Finally, the data bus coupler 401 and the power divider 402 are pressed into the cavity of the suspension device by a fixing clamp, and are fixed by a screw.

[0051] In order to reliably and effectively transmit high-bandwidth radio frequency signals to the suspension, the multi-line suspension system cable device selects a coaxial cable with a characteristic impedance of 50Ω and 75Ω to be connected to an SMA type radio frequency plug, and finally connected to the power divider 402 to complete the branching of the radio frequency signal line, as shown in Figure 5 The coaxial wire shielding layer is crimped in the shielding ring of the SMA type radio frequency plug, and after being connected to the power divider 402, it is connected through the shell to realize the continuity of the shielding whole and improve the shielding performance. The SMA type radio frequency plug is coated with thread glue in the thread to prevent loosening, and the outside is blown with DW double-wall heat shrink tube to further prevent the thread from loosening and provide external protection and insulation. The shell of the power divider 402 (except for the three threaded interfaces) is painted, coated with QH-15 anti-corrosion epoxy primer, and then coated with QFS-15 (black B99) weather-resistant matte polyurethane enamel, improving the ability to resist moisture, heat, mold, and salt spray.

[0052] In order to improve the overall electromagnetic compatibility of the multi-line suspension system cable device, the outermost part of the wire of the multi-line suspension system cable device is provided with an HTPQ wave suppression sleeve 5, and the shell is connected at 360°, so that the overall shielding layer of the wire is continuous. The outer part of the wire between the data bus coupler and the power divider 4 and the aircraft end electrical interface mechanism 2, the wire between the data bus coupler and the power divider 4 and the electrical suspension end electrical interface mechanism 7, the wire between the data bus coupler and the power divider 4 and the electrical connector 3, and the wire between the data bus coupler and the power divider 4 and the pull-off electrical connector 1 is provided with a wave suppression sleeve 5.

[0053] The beneficial effects of the embodiment of the present application are:

[0054] The multi-line suspension system cable device of the embodiment of the present application realizes the docking between the electrical connectors through the electrical interface mechanism, provides docking in place feedback signals, and provides a certain locking holding force to ensure that the electrical connection can reliably transmit signals in a high-velocity vibration environment; the rectangular connector has multiple transmission channels such as high-frequency cavities, low-frequency cavities, and air path channels, which can ensure the reliable transmission of electrical signals and air path pressure, and improve the modularization and integration level of the multi-line suspension system cable device; the multi-line suspension system cable device uses a data bus coupler and a power divider to branch 1553B data signals and high-bandwidth radio frequency signals respectively, and synchronously transmits the signals to the suspension, reduces wiring, improves the utilization rate of the electrical connector 3 hole group in a limited space, and realizes more functions.

[0055] Each of the embodiments in the specification is described in a progressive manner, and the same or similar parts between each embodiment can be referred to each other. Each embodiment focuses on the difference from other embodiments. In particular, for the method embodiment described later, since it corresponds to the system, the description is relatively simple, and the relevant parts refer to the part of the system embodiment.

[0056] The above description is only specific embodiments of the present application, but the protection scope of the present application is not limited thereto, any changes or replacements within the technical scope disclosed by the present application can be easily thought by those skilled in the art, and should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A multi-line suspension system cable arrangement, characterized by, The multi-line suspension system cable device comprises a rectangular connector (6), a data bus coupler and power divider (4), an aircraft end electrical interface (2), a suspension end electrical interface (7), a pull-off electrical connector (1) and an electrical connector (3), the rectangular connector (6) is fixed on the aircraft end electrical interface (2), an input end of the rectangular connector (6) is connected with the aircraft end electrical interface (2), a first output end of the rectangular connector (6) is connected to the pull-off electrical connector (1) through the data bus coupler and power divider (4), a second output end of the rectangular connector (6) is connected to the suspension end electrical interface (7) through the data bus coupler and power divider (4), and a third output end of the rectangular connector (6) is connected with the electrical connector (3). The data bus coupler and power divider (4) comprises a data bus coupler (401) and a power divider (402). The data bus coupler (401) comprises a coupler input end (4011) and two coupler output ends (4012), the coupler input end (4011) is connected with the rectangular connector (6), a first coupler output end (4012) is connected with the pull-off electrical connector (1), and a second coupler output end (4012) is connected with the suspension end electrical interface (7). The power divider (402) comprises an input end SMA radio frequency plug (4021) and two output end SMA radio frequency plugs (4022), the input end SMA radio frequency plug (4021) is connected with the rectangular connector (6), a first output end SMA radio frequency plug (4022) is connected with the pull-off electrical connector (1), and a second output end SMA radio frequency plug (4022) is connected with the suspension end electrical interface (7). The rectangular connector (6) comprises: a low-frequency cavity (601), low-frequency signals of the low-frequency cavity (601) are connected to the pull-off electrical connector (1) or the electrical connector (3) or the electrical connector (3) on the suspension end electrical interface (7) after being branched off; a high-frequency cavity (603), high-frequency signals of the high-frequency cavity (603) are connected to the pull-off electrical connector (1) or the electrical connector (3) on the suspension end electrical interface (7) after being branched off through the data bus coupler (401) and the power divider (402); an air path channel (602) and a pipe connecting piece (605), air path pressure is transmitted to an external suspension device through the air path channel (602) and the pipe connecting piece (605). The data bus coupler (401) is a SYMB / A type twin-line data bus coupler.

2. The multi-line hanger system cable arrangement of claim 1, wherein, The power divider (402) is an HDDS2SMAK-3 power divider.

3. The multi-line hanger system cable arrangement of claim 1, wherein, The multi-line suspension system cable device further comprises a wave-proof sleeve (5), the wave-proof sleeve (5) is sleeved outside the wires between the data bus coupler and power divider (4) and the aircraft end electrical interface (2), the wires between the data bus coupler and power divider (4) and the suspension end electrical interface (7), the wires between the data bus coupler and power divider (4) and the electrical connector (3), and the wires between the data bus coupler and power divider (4) and the pull-off electrical connector (1).

4. The multi-line hanger system cable arrangement of claim 1, wherein, ​ 5. The multi-line hanger system cable arrangement of claim 1, wherein, The multi-line suspension system cable device further comprises a fixed clamp (8), and the data bus coupler and the power divider (4) are fixed on the launching device through the fixed clamp (8).

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