CN113306735A - Aircraft hanging object control cable integrated system - Google Patents
Aircraft hanging object control cable integrated system Download PDFInfo
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- CN113306735A CN113306735A CN202110785902.0A CN202110785902A CN113306735A CN 113306735 A CN113306735 A CN 113306735A CN 202110785902 A CN202110785902 A CN 202110785902A CN 113306735 A CN113306735 A CN 113306735A
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- 238000004891 communication Methods 0.000 claims abstract description 39
- 238000012937 correction Methods 0.000 claims abstract description 20
- 238000001514 detection method Methods 0.000 claims abstract description 18
- 230000010354 integration Effects 0.000 claims description 11
- 238000012806 monitoring device Methods 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 5
- 238000013461 design Methods 0.000 abstract description 4
- 238000001125 extrusion Methods 0.000 description 2
- 238000007726 management method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/25—Pc structure of the system
- G05B2219/25257—Microcontroller
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Cable Transmission Systems, Equalization Of Radio And Reduction Of Echo (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The application belongs to the technical field of aircraft carry thing control system design, concretely relates to aircraft carry thing control cable integrated system, include: the radio frequency pipe controller is integrated with a bus controller; the bus controller is provided with three communication interfaces; each communication interface leads out a bus cable to be laid on the left wing, the fuselage and the right wing of the airplane respectively, and the bus cable is coupled out of a branch through a bus coupler and is connected to the mounting points of each hanging object on the corresponding part of the airplane; an airborne radar detection signal output end; the CC coaxial cable and the radio correction command cable are connected with the radio frequency pipe controller and the airborne radar detection signal output end; the radio frequency pipe controller switches the signal tee joint transmitted by the CC coaxial cable to the three communication interfaces and divides the signal power transmitted by the radio correction instruction cable to the three communication interfaces; each communication interface leads out a plurality of CC coaxial cable branches and radio correction command cable branches which are respectively connected with each mounting point of the corresponding part on the airplane.
Description
Technical Field
The application belongs to the technical field of design of an aircraft hanging object control system, and particularly relates to an aircraft hanging object control cable integrated system.
Background
At present, an aircraft carry object control system is designed to lead out a bus cable from a bus controller, the bus cable is sequentially laid through carry points of each carry object on the aircraft, and a branch is coupled out through a bus coupler and connected to each carry point, so that each carry object on the aircraft is controlled.
In addition, in order to access signals detected by an airborne radar to each on-board loading point of an airplane, the airplane on-board loading control system is designed with a CC coaxial cable and a radio correction command cable, wherein the CC coaxial cable is connected with the detection signal output end of the airborne radar and is branched and connected to each on-board loading point through a tee joint; the radio correction instruction cable is connected with the detection signal output end of the airborne radar and is connected to each mounting point in a branching mode through the power divider.
In addition, in order to access satellite positioning signals to the mounting points of each mounted object on the airplane, the airplane mounted object control system is designed with a satellite signal cable, and the satellite signal cable is connected with the satellite signal output end on the airplane and is connected to each mounting point in a branching mode through a power divider.
Still, in order to monitor the aircraft hanging thing in real time, have the video monitor in each hanging point design, each video monitor is connected with the video cable, and each video cable is connected to the airborne video output through the video switch and is shown.
The aircraft mounted object control system has the following defects:
1) the throwing control of various hung objects on the airplane is realized through the branch of one bus cable, the transmission rate on the bus is limited, and the throwing requirements of a plurality of hung objects and the like on the airplane cannot be met;
2) each hanging object and the hanging points thereof on the airplane are distributed on the left wing, the airplane body and the right wing, the positions of the hanging objects and the hanging points thereof are dispersed, bus cables led out from a bus controller are sequentially laid on the hanging points of each hanging object on the airplane, the bus cables need to be turned back and forth repeatedly, and the wiring is complicated;
3) the CC coaxial cable and the radio correction command cable led out from the detection signal output end of the airborne radar, the bus cable led out from the bus controller and the video cable connected to the video output end through the video switcher have larger differences in laying paths, further aggravate the complexity of wiring of the aircraft on-board cargo control system, lead the laying paths of the cables to be disordered and intertwined with each other, and are easy to have the fault conditions that a single cable falls off, breaks and is unstable in connection due to extrusion and pulling;
4) the bus controller, the bus coupler, the three-way interface, the power divider and the video switcher are scattered everywhere, so that unified management is inconvenient, and when a fault occurs, the fault is inconvenient to find.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft on-board control cable integration system to overcome or mitigate at least one aspect of the technical deficiencies known to exist.
The technical scheme of the application is as follows:
an aircraft on-hook control cable integration system, comprising:
the radio frequency pipe controller is integrated with a bus controller; the bus controller is provided with three communication interfaces; each communication interface leads out a bus cable to be laid on the left wing, the fuselage and the right wing of the airplane respectively, and the bus cable is coupled out of a branch through a bus coupler and is connected to the mounting points of each hanging object on the corresponding part of the airplane;
an airborne radar detection signal output end;
the CC coaxial cable is connected with the radio frequency pipe controller and the airborne radar detection signal output end; the radio frequency pipe controller switches the signal tee joint transmitted by the CC coaxial cable to three communication interfaces; each communication interface leads out a plurality of CC coaxial cable branches which are respectively connected with each mounting point of the corresponding part on the airplane;
the radio correction command cable is connected with the radio frequency pipe controller and the airborne radar detection signal output end; the radio frequency pipe controller divides the signal power transmitted by the radio correction instruction cable into three communication interfaces; each communication interface leads out a plurality of radio correction command cable branches which are respectively connected with each mounting point of the corresponding part on the airplane.
According to at least one embodiment of the present application, in the aircraft on-load control cable integrated system, further comprising:
an onboard satellite signal output terminal;
the satellite signal cable is connected with the radio frequency pipe controller and the airborne radar detection signal output end; the radio frequency pipe controller divides the signal power transmitted by the satellite signal cable into three communication interfaces; each communication interface leads out a plurality of satellite signal cable branches which are respectively connected with each mounting point of the corresponding part on the airplane.
According to at least one embodiment of the present application, in the aircraft on-hook control cable integration system, a video switcher is integrated on the radio frequency controller;
each communication interface is connected with the video monitors of the mounting points of the corresponding parts on the airplane through a plurality of video cable branches;
the aircraft on-hook thing control cable integrated system still includes:
an airborne video output end;
the video cable is connected with the radio frequency pipe controller and the airborne video output end and is connected with each video cable branch through the video switcher.
According to at least one embodiment of the application, in the aircraft on-board control cable integrated system, the bus cable, the CC coaxial cable, the radio correction command cable, the satellite signal cable and the video cable corresponding to each communication interface are integrated into a wire harness.
According to at least one embodiment of the present application, in the aircraft on-load control cable integrated system, further comprising:
and a special electric connector is designed corresponding to each wire harness, and the disconnected parts of each wire harness are connected through the corresponding special electric connectors.
According to at least one embodiment of the application, in the integrated system of aircraft on-load control cables described above, each bus cable is connected to the bus cable monitoring device through a bus coupler coupling-out branch, and the bus cable monitoring device monitors transmission data of each bus cable.
According to at least one embodiment of the present application, in the integrated system of aircraft on-board control cables, each bus cable and its branch coupled out by the bus coupler are double-margin.
Drawings
FIG. 1 is a schematic diagram of an integrated aircraft on-load control cable system provided in an embodiment of the present application;
wherein:
1-radio frequency controller; 2-a bus cable; 3-mounting points; 4-airborne radar detection signal output end; 5-CC coaxial cable; 6-CC coaxial cable branch; 7-radio correction command cable; 8-radio modifying command cable branches; 9-satellite signal output terminal on the machine; 10-satellite signal cable; 11-satellite signal cable branch; 12-video cable branch; 3-airborne video output end; 14-video cable; 15-dedicated electrical connectors; 16-a bus monitoring device; 17-bus coupler.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1.
An aircraft on-hook control cable integration system, comprising:
the radio frequency pipe controller 1 is integrated with a bus controller; the bus controller is provided with three communication interfaces; each communication interface leads out a bus cable 2 which is laid on the left wing, the fuselage and the right wing of the airplane respectively, and is coupled out of a branch through a bus coupler 17 to be connected to the hanging points 3 of each hanging object on the corresponding part of the airplane;
an airborne radar detection signal output end 4;
the CC coaxial cable 5 is connected with the radio frequency pipe controller 1 and the airborne radar detection signal output end 4; the radio frequency pipe controller 1 switches the signal tee joint transmitted by the CC coaxial cable 5 to three communication interfaces; each communication interface leads out a plurality of CC coaxial cable branches 6 which are respectively connected with each mounting point 3 of the corresponding part on the airplane;
the radio correction command cable 7 is connected with the radio frequency pipe controller 1 and the airborne radar detection signal output end 4; the radio frequency controller 1 divides the signal power transmitted by the radio correction instruction cable 7 into three communication interfaces; each communication interface leads out a plurality of radio correction command cable branches 8 which are respectively connected with each mounting point 3 of the corresponding part on the airplane.
In some optional embodiments, in the above aircraft on-hook control cable integrated system, further comprising:
an onboard satellite signal output terminal 9;
the satellite signal cable 10 is connected with the radio frequency pipe controller 1 and the airborne radar detection signal output end 4; the radio frequency pipe controller 1 divides the signal power transmitted by the satellite signal cable 10 into three communication interfaces; each communication interface leads out a plurality of satellite signal cable branches 11 which are respectively connected with each mounting point 3 of the corresponding part on the airplane.
In some optional embodiments, in the above-mentioned aircraft hanging cargo control cable integrated system, a video switcher is integrated on the video pipe controller 1;
each communication interface is connected with the video monitors of the mounting points 3 at the corresponding part on the airplane through a plurality of video cable branches 12;
the aircraft on-hook thing control cable integrated system still includes:
an onboard video output 13;
and the video cable 14 is connected with the radio frequency controller 1 and the airborne video output end 12 and is connected to each video cable branch 12 through a video switcher.
In some optional embodiments, in the above-mentioned aircraft on-board control cable integrated system, the bus cable 2, the CC coaxial cable 5, the radio correction instruction cable 7, the satellite signal cable 10, and the video cable 14 corresponding to each communication interface are integrated into a wire harness.
In some optional embodiments, in the above aircraft on-hook control cable integrated system, further comprising:
the special electric connector 15 is designed corresponding to each wire harness, and the disconnection parts of each wire harness are connected through the corresponding special electric connector 15, so that the connection of the disconnection parts of the wire harnesses is rapid and convenient.
In some optional embodiments, in the above-mentioned integrated system for aircraft on-load control cables, the bus monitoring device 16 is connected to the bus monitoring device 16 by coupling out each bus cable 2 via the bus coupler 17, and the bus monitoring device 16 monitors the transmission data of each bus cable 2.
In some alternative embodiments, in the integrated system of aircraft on-board control cables described above, each bus cable 2 and its branch coupled out by the bus coupler 17 are double-margin.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
For the aircraft hanging object control cable integrated system disclosed in the above embodiment, it can be understood by those skilled in the art that three bus cables 2 are led out from three communication interfaces of the radio frequency controller 1, and are respectively coupled out of the branches through the bus coupler 17 to be connected with the hanging points 3 of hanging objects at the left wing, the fuselage and the right wing of the aircraft, so as to realize control of throwing of the hanging objects on the aircraft, and the system has a relatively high transmission rate, and can meet the requirement of throwing of a plurality of hanging objects and the like on the aircraft to a certain extent.
For the integrated system of the aircraft hanging object control cable disclosed in the above embodiment, it can be further understood by those skilled in the art that each hanging object and its hanging points on the aircraft are relatively and intensively distributed at the left wing, fuselage and right wing of the aircraft, three bus cables 2 are led out from three communication interfaces of the radio frequency tube controller 1, and are respectively coupled out of the branch by the bus coupler 17 to be connected with the hanging points 3 of each hanging object at the left wing, fuselage and right wing of the aircraft, so that the bus cables 2 can be prevented from being turned back and forth and repeatedly laid between the left wing, fuselage and right wing of the aircraft, and the complexity of wiring can be effectively reduced.
For the integrated system of aircraft hanging object control cable disclosed in the above embodiment, it can be further understood by those skilled in the art that three bus cables 2 are led out from three communication interfaces of the radio frequency controller 1, and are respectively coupled out of branches through the bus coupler 17 to be connected with the hanging points 3 of the hanging objects on the left wing, the fuselage and the right wing of the aircraft, and each CC coaxial cable 5, the radio correction command cable 7, the satellite signal cable 10 and the video cable 14 corresponding to each communication interface are respectively connected with each hanging point 3 on the left wing, the fuselage and the right wing of the aircraft, and are substantially the same as the routing path of the corresponding bus cable 2, so that the complexity of routing can be further reduced, the cable routing paths are ordered, the cables are prevented from being entangled with each other, and the single cable is prevented from falling off due to extrusion and pulling, Failure conditions of fracture and unstable connection.
To the aircraft carry thing control cable integrated system disclosed in the above-mentioned embodiment, the skilled person in the art can also understand that, the radio frequency pipe accuse ware 1 is integrated with the function of bus controller, tee bend interface, merit divider and video switch, avoids appearing bus controller, tee bend interface, merit divider and video switch dispersion everywhere, and the unified management of being not convenient for, and do not need a plurality of tee bend interfaces, merit divider, the complexity of system has been reduced, when breaking down, can be quick carry out troubleshooting.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (7)
1. An aircraft on-hook control cable integration system, comprising:
the radio frequency pipe controller (1) is integrated with a bus controller; the bus controller is provided with three communication interfaces; each communication interface leads out a bus cable (2) to be respectively laid on the left wing, the fuselage and the right wing of the airplane, and a branch is coupled out by a bus coupler (17) to be connected to each hanging point (3) of each hanging object on the corresponding part of the airplane;
an airborne radar detection signal output end (4);
the CC coaxial cable (5) is connected with the radio frequency pipe controller (1) and the airborne radar detection signal output end (4); the radio frequency pipe controller (1) switches the signal tee joint transmitted by the CC coaxial cable (5) to the three communication interfaces; each communication interface leads out a plurality of CC coaxial cable branches (6) which are respectively connected with each mounting point (3) of the corresponding part on the airplane;
the radio correction command cable (7) is connected with the radio frequency pipe controller (1) and the airborne radar detection signal output end (4); the radio frequency pipe controller (1) divides the signal power transmitted by the radio correction instruction cable (7) into three communication interfaces; each communication interface leads out a plurality of radio correction command cable branches (8) which are respectively connected with each mounting point (3) of the corresponding part on the airplane.
2. The aircraft on-board control cable integration system of claim 1,
further comprising:
an onboard satellite signal output terminal (9);
the satellite signal cable (10) is connected with the radio frequency pipe controller (1) and the airborne radar detection signal output end (4); the radio frequency pipe controller (1) divides the signal power transmitted by the satellite signal cable (10) into three communication interfaces; each communication interface leads out a plurality of satellite signal cable branches (11) which are respectively connected with each mounting point (3) of the corresponding part on the airplane.
3. The aircraft on-board control cable integration system of claim 2,
a video switcher is integrated on the radio frequency pipe controller (1);
each communication interface is connected with the video monitors of the mounting points (3) at the corresponding part on the airplane through a plurality of video cable branches (12);
the aircraft on-hook thing control cable integrated system still includes:
an onboard video output (13);
and the video cable (14) is connected with the radio frequency pipe controller (1) and the airborne video output end (12), and is connected with each video cable branch (12) through the video switcher.
4. The aircraft on-hook control cable integration system of claim 3,
and each bus cable (2), CC coaxial cable (5), radio correction instruction cable (7), satellite signal cable (10) and video cable (14) corresponding to each communication interface are integrated into a wire harness.
5. The aircraft on-hook control cable integration system of claim 4,
further comprising:
a special electric connector (15) is designed corresponding to each wire harness, and the disconnection parts of each wire harness are connected through the corresponding special electric connector (15).
6. The aircraft on-board control cable integration system of claim 1,
each bus cable (2) is coupled out of a branch through a bus coupler (17) and is connected to the bus cable monitoring device (16), and the bus cable monitoring device (16) monitors the transmission data of each bus cable (2).
7. The aircraft on-hook control cable integration system of claim 6,
each bus cable (2) and its branch coupled out by a bus coupler (17) are double-margin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110785902.0A CN113306735B (en) | 2021-07-12 | 2021-07-12 | Aircraft mount control cable integrated system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110785902.0A CN113306735B (en) | 2021-07-12 | 2021-07-12 | Aircraft mount control cable integrated system |
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| Publication Number | Publication Date |
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| CN113306735A true CN113306735A (en) | 2021-08-27 |
| CN113306735B CN113306735B (en) | 2023-07-21 |
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| CN202110785902.0A Active CN113306735B (en) | 2021-07-12 | 2021-07-12 | Aircraft mount control cable integrated system |
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2021
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| CN113306735B (en) | 2023-07-21 |
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