CN113306735B - Aircraft mount control cable integrated system - Google Patents
Aircraft mount control cable integrated system Download PDFInfo
- Publication number
- CN113306735B CN113306735B CN202110785902.0A CN202110785902A CN113306735B CN 113306735 B CN113306735 B CN 113306735B CN 202110785902 A CN202110785902 A CN 202110785902A CN 113306735 B CN113306735 B CN 113306735B
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- cable
- aircraft
- bus
- radio frequency
- frequency controller
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- 238000004891 communication Methods 0.000 claims abstract description 39
- 238000012937 correction Methods 0.000 claims abstract description 22
- 238000001514 detection method Methods 0.000 claims abstract description 15
- 238000010168 coupling process Methods 0.000 claims abstract description 7
- 238000005859 coupling reaction Methods 0.000 claims abstract description 7
- 230000008878 coupling Effects 0.000 claims abstract description 6
- 230000010354 integration Effects 0.000 claims description 11
- 238000012806 monitoring device Methods 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 5
- 238000013461 design Methods 0.000 abstract description 3
- 238000001125 extrusion Methods 0.000 description 2
- 238000007726 management method Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
Classifications
-
- 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
Landscapes
- 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 aircraft mount control system design technical field, concretely relates to aircraft mount control cable integrated system, include: the radio frequency controller is integrated with a bus controller; the bus controller is configured with three communication interfaces; each communication interface is led out of a bus cable to be respectively laid to the left wing, the fuselage and the right wing of the aircraft, and the bus coupler is used for coupling out the mounting points of each mounting object which is branched and connected to the corresponding part on the aircraft; the airborne radar detection signal output end; the CC coaxial cable and the radio correction command cable are connected with the radio frequency controller and the airborne radar detection signal output end; the radio frequency controller switches the signal tee joint transmitted by the CC coaxial cable to three communication interfaces, and divides the signal power transmitted by the radio correction instruction cable to three communication interfaces; and each communication interface is led out of a plurality of CC coaxial cable branches and radio correction instruction cable branches, and the CC coaxial cable branches and the radio correction instruction cable branches are respectively connected with each mounting point of the corresponding part on the aircraft.
Description
Technical Field
The application belongs to the technical field of aircraft mount control system design, and particularly relates to an aircraft mount control cable integrated system.
Background
At present, an aircraft mount control system is designed to lead out a bus cable from a bus controller, the bus cable is sequentially laid to pass through mounting points of all mounts on an aircraft, and is coupled to all mounting points through a bus coupler out-coupling branch, so that control of all mounts on the aircraft is realized.
In addition, in order to access signals detected by the airborne radar at the mounting points of all the mounted objects on the aircraft, the aircraft mounted object control system is designed with a CC coaxial cable and a radio correction command cable, wherein the CC coaxial cable is connected with the output end of the detection signals of the airborne radar and is branched and connected to all the mounting points through a tee joint; the radio correction command cable is connected with the detection signal output end of the airborne radar and is branched and connected to each mounting point through the power divider.
In order to access satellite positioning signals to the mounting points of the various mounting objects on the aircraft, the aircraft mounting object control system is provided with a satellite signal cable which is connected with the satellite signal output end on the aircraft and is branched and connected to the mounting points through a power divider.
In addition, in order to monitor the aircraft mounted object in real time, video monitors are designed at all mounting points, all video monitors are connected with video cables, and all video cables are connected to an onboard video output end through video switches for displaying.
The aircraft mount control system has the following defects:
1) The control of the throwing of each mount on the aircraft 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 mounts on the aircraft and the like can not be met;
2) Each object to be mounted on the aircraft and mounting points thereof are distributed on the left wing, the fuselage and the right wing, the positions are dispersed, bus cables led out from the bus controller are sequentially laid to pass through the mounting points of each object to be mounted on the aircraft, the objects need to be repeatedly turned back, the layout is repeated, and the routing is complicated;
3) The CC coaxial cable led out from the airborne radar detection signal output end and the radio correction instruction cable thereof, 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 difference in laying paths, so that the complexity of wiring of the aircraft mount control system is further increased, the cable laying paths are disordered, the cables are mutually entangled, and the fault conditions of falling, breakage and unstable connection of a single cable due to extrusion and pulling are extremely easy to occur;
4) The bus controller, the bus coupler, the tee joint interface, the power divider and the video switcher are distributed in all positions, so that unified management is inconvenient, and troubleshooting is inconvenient when faults occur.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft payload control cable integration system that overcomes or mitigates at least one of the known technical drawbacks.
The technical scheme of the application is as follows:
an aircraft payload control cable integration system, comprising:
the radio frequency controller is integrated with a bus controller; the bus controller is configured with three communication interfaces; each communication interface is led out of a bus cable to be respectively laid to the left wing, the fuselage and the right wing of the aircraft, and the bus coupler is used for coupling out the mounting points of each mounting object which is branched and connected to the corresponding part on the aircraft;
the airborne radar detection signal output end;
the CC coaxial cable is connected with the radio frequency controller and the airborne radar detection signal output end; the radio frequency controller three-way switches the signal 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 aircraft;
the radio correction command cable is connected with the radio frequency controller and the airborne radar detection signal output end; the radio frequency controller divides signal power transmitted by the radio correction instruction cable into three communication interfaces; and each communication interface is led out of a plurality of radio correction instruction cable branches and respectively connected with each mounting point of the corresponding part on the aircraft.
According to at least one embodiment of the present application, in the aircraft mount control cable integrated system described above, the method further includes:
an onboard satellite signal output;
the satellite signal cable is connected with the radio frequency controller and the on-board satellite signal output end; the radio frequency controller divides signal power transmitted by the satellite signal cable into three communication interfaces; and 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 aircraft.
According to at least one embodiment of the present application, in the aircraft mount control cable integrated system described above, the radio frequency controller is integrated with a video switcher;
each communication interface is connected with a video monitor of each mounting point of the corresponding part on the aircraft through a plurality of video cable branches;
the aircraft payload control cable integration system further includes:
the onboard video output end;
the video cable is connected with the radio frequency controller and the onboard video output end and is connected with each video cable branch through the video switcher.
According to at least one embodiment of the present application, in the aircraft mount control cable integrated system, the bus cables, the CC coaxial cables, the radio correction command cables, the satellite signal cables, and the video cables corresponding to each communication interface are integrated into a wire harness.
According to at least one embodiment of the present application, in the aircraft mount control cable integrated system described above, the method further includes:
a special electric connector is designed corresponding to each wire harness, and the disconnection parts of each wire harness are connected through the corresponding special electric connector.
According to at least one embodiment of the present application, in the aircraft mount control cable integrated system, the bus monitoring device is configured to monitor transmission data of each bus cable, wherein each bus cable is connected to the bus monitoring device through a branch coupled by a bus coupler.
According to at least one embodiment of the present application, in the aircraft payload control cable integrated system described above, each bus cable and its branches coupled out by the bus coupler are double-tolerant.
Drawings
FIG. 1 is a schematic diagram of an aircraft mount control cable integration system provided in an embodiment of the present application;
wherein:
1-a radio frequency controller; a 2-bus cable; 3-mounting points; 4-the detection signal output end of the airborne radar; 5-CC coaxial cable; 6-CC coaxial cable branches; 7-a radio correction instruction cable; 8-radio correction instruction cable branches; 9-on-board satellite signal output; 10-satellite signal cable; 11-satellite signal cable branches; 12-video cable branches; 3-an onboard video output; 14-video cable; 15-a special electrical connector; 16-bus monitoring device; 17-bus coupler.
For the purpose of better illustrating the embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions; further, the drawings are for illustrative purposes, wherein the terms describing the positional relationship are limited to the illustrative description only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below in conjunction with fig. 1.
An aircraft payload control cable integration system, comprising:
the radio frequency controller 1 is integrated with a bus controller; the bus controller is configured with three communication interfaces; each communication interface leads out a bus cable 2 which is respectively laid to the left wing, the fuselage and the right wing of the aircraft, and the bus coupler 17 is used for coupling out the mounting points 3 of each mounting object which are branched and connected to the corresponding part on the aircraft;
the airborne radar detection signal output end 4;
the CC coaxial cable 5 is connected with the radio frequency controller 1 and the airborne radar detection signal output end 4; the radio frequency controller 1 three-way switches the signal 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 at the corresponding position on the aircraft;
the radio correction command cable 7 is connected with the radio frequency 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 command cable 7 into three communication interfaces; and each communication interface is led out to a plurality of radio correction instruction cable branches 8 which are respectively connected with each mounting point 3 of the corresponding part on the aircraft.
In some optional embodiments, the aircraft mount control cable integrated system further includes:
an onboard satellite signal output 9;
the satellite signal cable 10 is connected with the radio frequency controller 1 and the on-board satellite signal output end 9; the radio frequency controller 1 divides the signal power transmitted by the satellite signal cable 10 into three communication interfaces; and each communication interface is led out of a plurality of satellite signal cable branches 11 which are respectively connected with each mounting point 3 at the corresponding position on the aircraft.
In some alternative embodiments, in the above-mentioned aircraft mount control cable integrated system, the radio frequency controller 1 is integrated with a video switcher;
each communication interface is connected with the video monitor of each mounting point 3 of the corresponding part on the aircraft through a plurality of video cable branches 12;
the aircraft payload control cable integration system further includes:
an on-board video output 13;
the video cable 14 is connected with the radio frequency controller 1 and the onboard video output end 13, and is connected with each video cable branch 12 through a video switcher.
In some alternative embodiments, in the aircraft payload control cable integration system described above, the respective bus cables 2, CC coaxial cables 5, radio correction command cables 7, satellite signal cables 10, video cables 14 corresponding to each communication interface are grouped into bundles.
In some optional embodiments, the aircraft mount control cable integrated system further includes:
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 quick and convenient.
In some alternative embodiments, in the aircraft payload control cable integration system described above, bus guardian devices 16, each bus cable 2 is coupled out of the branch via bus coupler 17 to bus guardian device 16, and bus guardian device 16 monitors the transmission data of each respective bus cable 2.
In some alternative embodiments, in the aircraft payload control cable integration system described above, each bus cable 2 and its branches coupled out by bus coupler 17 are double-ended.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
For the aircraft mount 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 to the mount points 3 of each mount on the left wing, the fuselage and the right wing of the aircraft through the bus coupler 17, so that the control of the release of each mount on the aircraft is realized, the relatively high transmission rate is realized, and the release requirements of a plurality of mounts on the aircraft can be met to a certain extent.
For the aircraft mount control cable integrated system disclosed in the above embodiment, it may be further understood by those skilled in the art that each mount and its mounting point on the aircraft are relatively and intensively distributed at the left wing, the fuselage and the right wing of the aircraft, three bus cables 2 are designed to be led out from three communication interfaces of the radio frequency controller 1, and the branches are coupled to the mounting points 3 of each mount at the left wing, the fuselage and the right wing of the aircraft through bus couplers 17, so that the reciprocal turn-back of the bus cables 2 between the left wing, the fuselage and the right wing of the aircraft can be avoided, and the repeated laying can effectively reduce the complexity of routing.
For the aircraft mount control cable integrated system disclosed in the above embodiment, it may be further understood by those skilled in the art that, on the basis of designing three bus cables 2 led out from three communication interfaces of the radio frequency controller 1 and respectively coupling out branches through the bus coupler 17 to be connected with mounting points 3 of each mount of the left wing, the fuselage and the right wing of the aircraft, 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 designed to be respectively connected with each mounting point 3 of the left wing, the fuselage and the right wing of the aircraft, and are approximately the same as the routing paths of the corresponding bus cables 2, so that the routing complexity can be further reduced, the routing paths of the cables are more orderly, the cables are prevented from being entangled with each other, and the fault conditions of falling, breakage and unstable connection of the single cable caused by extrusion and pulling are prevented.
For the aircraft mount control cable integrated system disclosed in the above embodiment, those skilled in the art can also understand that the functions of the bus controller, the tee joint interface, the power divider and the video switcher are integrated on the radio frequency controller 1, so that the bus controller, the tee joint interface, the power divider and the video switcher are prevented from being scattered everywhere, the unified management is inconvenient, a plurality of tee joint interfaces and power dividers are not needed, the complexity of the system is reduced, and when faults occur, the fault investigation can be performed rapidly.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (7)
1. An aircraft payload control cable integration system, comprising:
the radio frequency controller (1) is integrated with a bus controller; the bus controller is configured with three communication interfaces; each communication interface is led out of a bus cable (2) to be laid to the left wing, the fuselage and the right wing of the aircraft respectively, and the bus coupler (17) is used for coupling out the mounting points (3) of each mounting object which are branched and connected to the corresponding part on the aircraft;
an airborne radar detection signal output end (4);
the CC coaxial cable (5) is connected with the radio frequency controller (1) and the airborne radar detection signal output end (4); the radio frequency 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) at the corresponding position on the aircraft;
a radio correction command cable (7) connected with the radio frequency 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 command cable (7) to three communication interfaces; and each communication interface is led out of a plurality of radio correction instruction cable branches (8) which are respectively connected with each mounting point (3) of the corresponding part on the aircraft.
2. The aircraft mount control cable integrated system according to claim 1 wherein,
further comprises:
an onboard satellite signal output (9);
a satellite signal cable (10) connected with the radio frequency controller (1) and the on-board satellite signal output end (9); the radio frequency controller (1) divides signal power transmitted by the satellite signal cable (10) to three communication interfaces; and each communication interface is led out of a plurality of satellite signal cable branches (11) which are respectively connected with each mounting point (3) at the corresponding position on the aircraft.
3. The aircraft mount control cable integrated system according to claim 2 wherein,
the radio frequency controller (1) is integrated with a video switcher;
each communication interface is connected with a video monitor of each mounting point (3) of a corresponding part on the aircraft through a plurality of video cable branches (12);
the aircraft mount control cable integrated system further comprises:
an on-board video output (13);
and the video cable (14) is connected with the radio frequency controller (1) and the airborne video output end (13), and is connected with each video cable branch (12) through the video switcher.
4. The aircraft payload control cable integration system of claim 3,
the respective bus cables (2), CC coaxial cables (5), radio correction command cables (7), satellite signal cables (10), video cables (14) corresponding to each of the communication interfaces are grouped into a harness.
5. The aircraft mount control cable integrated system according to claim 4 wherein,
further comprises:
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 mount control cable integrated system according to claim 1 wherein,
and the bus monitoring devices (16) are connected to the bus monitoring devices (16) through the bus coupler (17) coupling out branches of each bus cable (2), and the bus monitoring devices (16) monitor transmission data of each bus cable (2).
7. The aircraft mount control cable integrated system according to claim 6 wherein,
each of the bus cables (2) and the branches coupled out by the bus coupler (17) are double-tolerant.
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113306735A CN113306735A (en) | 2021-08-27 |
| CN113306735B true CN113306735B (en) | 2023-07-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110785902.0A Active CN113306735B (en) | 2021-07-12 | 2021-07-12 | Aircraft mount control cable integrated system |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN209814278U (en) * | 2018-12-03 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | External airborne control system with communication function |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5992290A (en) * | 1997-04-09 | 1999-11-30 | Cubic Defense Systems, Inc. | Aircraft interface device and crossover cable kit |
| US20040018778A1 (en) * | 2002-07-23 | 2004-01-29 | Walter Easterbrook | Systems and methods for connecting components in an entertainment system |
| US20170355449A1 (en) * | 2016-06-10 | 2017-12-14 | Goodrich Aerospace Services Private Limited | Electrical architecture for slat/flap control using smart sensors and effectors |
| CN109639291A (en) * | 2018-10-25 | 2019-04-16 | 中国航空工业集团公司洛阳电光设备研究所 | A kind of modular airborne stores management system HB1 route selection network module |
| CN112666856B (en) * | 2020-12-09 | 2022-09-27 | 浙江吉利控股集团有限公司 | Satellite load subsystem |
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2021
- 2021-07-12 CN CN202110785902.0A patent/CN113306735B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN209814278U (en) * | 2018-12-03 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | External airborne control system with communication function |
Non-Patent Citations (1)
| Title |
|---|
| 某型飞机吊舱控制信号异常分析与整改;杨武;电磁干扰抑制技术(第5期);第65-67页 * |
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| CN113306735A (en) | 2021-08-27 |
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