CN105373023A - Avionics integration test integrated control assembly - Google Patents
Avionics integration test integrated control assembly Download PDFInfo
- Publication number
- CN105373023A CN105373023A CN201510827349.7A CN201510827349A CN105373023A CN 105373023 A CN105373023 A CN 105373023A CN 201510827349 A CN201510827349 A CN 201510827349A CN 105373023 A CN105373023 A CN 105373023A
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- avionics
- avionic
- display matrix
- detection system
- joint test
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- 238000012360 testing method Methods 0.000 title claims abstract description 61
- 230000010354 integration Effects 0.000 title abstract 12
- 238000001514 detection method Methods 0.000 claims abstract description 37
- 239000011159 matrix material Substances 0.000 claims abstract description 32
- 238000004088 simulation Methods 0.000 claims description 11
- 230000005284 excitation Effects 0.000 claims description 9
- 238000004132 cross linking Methods 0.000 claims description 4
- 238000012544 monitoring process Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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- 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
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Controls And Circuits For Display Device (AREA)
Abstract
The invention discloses an avionics integration test integrated control assembly. The avionics integration test integrated control assembly comprises an avionics detection system which is connected with an aircraft avionics system, a display matrix system which is connected with the avionics detection system, an integration test control system which is connected with the avionics detection system and the display matrix system respectively, and a cockpit control system which is connected with the integration test control system; the avionics detection system is used for detecting the working state of the aircraft avionics system; the integration test control system is used for controlling the work of the avionics detection system and the display matrix system; the cockpit control system is used for providing control instructions for the integration test control system; and the display matrix system is used for integrating and displaying images. According to the avionics integration test integrated control assembly of the invention, the systems are organically linked together, so that the systems can cooperate with each other so as to complete avionics integration test tasks. Compared with the prior art, the avionics integration test integrated control assembly can facilitate operation and monitoring of integration test personnel, reduce the burden of the integration test personnel and improve work efficiency.
Description
Technical Field
The invention relates to the technical field of airplanes, in particular to an integrated control assembly for an avionic combined test.
Background
In the past avionics joint test process, various simulation excitation devices, comprehensive test devices and joint test control computers are often isolated, and joint testers in a cabin lack good monitoring and control over various simulation excitation test devices, operate and check everywhere, and waste time and labor.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned problems of the prior art.
Disclosure of Invention
It is an object of the present invention to provide an avionics combined control assembly to overcome or at least alleviate at least one of the above-mentioned problems of the prior art.
In order to achieve the above object, the present invention provides an avionics combined test integrated control assembly, which comprises: the avionic detection system is connected with the airplane avionic system; the display matrix system is connected with the avionic detection system; the joint test control system is respectively connected with the avionic detection system and the display matrix system; the cabin control system is connected with the joint test control system; the avionic detection system is used for detecting the working state of an aircraft avionic system; the joint test control system is used for controlling the avionic detection system and the display matrix to work; the cabin control system is used for providing a control instruction for the joint test control system; the display matrix system is used for integrating and displaying pictures.
Preferably, the display matrix system comprises: a plurality of displays connected to each other in a tiled manner; the video concatenation treater, the video concatenation treater is connected with a plurality of displays, avionics detecting system and the joint test control system that splice each other and be connected respectively, the video concatenation treater is used for distributing the display signal that avionics detecting system and joint test control system transmitted.
Preferably, the avionics detection system comprises: the simulation excitation equipment is respectively connected with the aircraft avionic system and the video splicing processor and is used for providing an excitation source or a simulation cross-linking system for the aircraft avionic system; the comprehensive test equipment is respectively connected with the aircraft avionic system and the video splicing processor and is used for testing the aircraft avionic system; and the cabin monitor is connected with the video splicing processor and is used for displaying the display information transmitted by the video splicing processor in real time.
Preferably, the joint trial control system includes: the joint test control upper computer is respectively connected with the avionic detection system and the display matrix system and is used for controlling the avionic detection system to work and transmitting display signals to the display matrix system; and the control terminal is used for being connected with the joint test control upper computer and transmitting a control instruction to the joint test control upper computer.
Preferably, the number of the displays tiled to each other in the display matrix system is 6.
The avionics integrated control assembly organically connects the avionics detection system, the display matrix system, the integrated test control system and the cockpit control system together, and enables the systems to be mutually matched, so that an avionics integrated test task is completed.
Drawings
Fig. 1 is a schematic connection diagram of an integrated avionics integrated control assembly according to a first embodiment of the present invention.
Reference numerals:
| 1 | avionics detection system | 4 | Joint test control system |
| 2 | Aircraft avionics system | 5 | Cabin control system |
| 3 | Display matrix system |
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
Fig. 1 is a schematic connection diagram of an integrated avionics integrated control assembly according to a first embodiment of the present invention.
The avionics integrated control assembly shown in fig. 1 comprises an avionics detection system 1, a display matrix system 3, an integrated test control system 4 and a cockpit control system 5. The avionic detection system 1 is connected with the aircraft avionic system 2; the display matrix system 3 is connected with the avionic detection system 1; the joint test control system 4 is respectively connected with the avionics detection system 1 and the display matrix system 3; the cabin control system 5 is connected with the joint test control system 4; the avionic detection system 1 is used for detecting the working state of an aircraft avionic system; the joint test control system 4 is used for controlling the avionics detection system 1 and the display matrix system 3 to work; the cabin control system 5 is used for providing a control instruction for the joint test control system 4; the display matrix system 3 is used for integrating and displaying pictures.
In the present embodiment, the display matrix system 3 includes: the display system comprises a plurality of displays connected with each other in a splicing mode and a video splicing processor, wherein the video splicing processor is respectively connected with the displays connected with each other in a splicing mode, the avionic detection system 1 and the joint test control system 4, and the video splicing processor is used for distributing display signals transmitted by the avionic detection system 1 and the joint test control system 4.
In this embodiment, the avionics detection system 1 includes a simulation excitation device, a cockpit monitor and a comprehensive test device, the simulation excitation device is respectively connected with the aircraft avionics system 2 and the video stitching processor, and is used to provide an excitation source or a simulation cross-linking system for the aircraft avionics system 2, specifically, the simulation cross-linking system is used to provide simulation in the actual flight process of the aircraft, for example, the stress condition encountered by the aircraft or the condition encountered in windy and snowy days; the comprehensive test equipment is respectively connected with the aircraft avionics system 2 and the video splicing processor and is used for testing the aircraft avionics system 2;
and the cockpit monitor is connected with the video splicing processor and is used for displaying the display information transmitted by the video splicing processor in real time.
In this embodiment, the joint test control system 4 includes a joint test control upper computer and a control terminal, the joint test control upper computer is respectively connected with the avionics detection system 1 and the display matrix system 3, and the joint test control upper computer is used for controlling the avionics detection system 1 to work and transmitting a display signal to the display matrix system 3; and the control terminal is used for being connected with the joint test control upper computer and transmitting a control instruction for the joint test control upper computer.
The number of displays tiled to each other in the display matrix system described in this embodiment is 6. It is understood that the number of the display devices connected to each other by splicing can be set according to the requirement. E.g., 2, 3, or more.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (5)
1. An avionics integrated control assembly, comprising:
the avionic detection system (1), the avionic detection system (1) is connected with the aircraft avionic system (2);
the display matrix system (3), the display matrix system (3) is connected with the avionics detection system (1);
the joint test control system (4), the joint test control system (4) is respectively connected with the avionic detection system (1) and the display matrix system (3);
the cabin control system (5), the cabin control system (5) is connected with the joint test control system (4); wherein,
the avionic detection system (1) is used for detecting the working state of an aircraft avionic system; the joint test control system (4) is used for controlling the avionics detection system (1) and the display matrix system (3) to work; the cabin control system (5) is used for providing a control instruction for the joint test control system (4); the display matrix system (3) is used for integrating and displaying pictures.
2. An avionics integrated control assembly according to claim 1, characterized in that the display matrix system (3) comprises:
a plurality of displays connected to each other in a tiled manner;
the video splicing processor is respectively connected with a plurality of displays connected with each other in a splicing manner, the avionics detection system (1) and the joint test control system (4), and the video splicing processor is used for distributing display signals transmitted by the avionics detection system (1) and the joint test control system (4).
3. An avionics integrated control assembly according to claim 2, characterized in that the avionics detection system (1) comprises:
the simulation excitation equipment is respectively connected with the aircraft avionic system (2) and the video splicing processor and is used for providing an excitation source or a simulation cross-linking system for the aircraft avionic system (2);
the comprehensive test equipment is respectively connected with the aircraft avionic system (2) and the video splicing processor and is used for testing the aircraft avionic system (2);
and the cabin monitor is connected with the video splicing processor and is used for displaying the display information transmitted by the video splicing processor in real time.
4. An avionics integrated pilot control assembly according to claim 1, characterized in that the pilot control system (4) comprises:
the joint test control upper computer is respectively connected with the avionic detection system (1) and the display matrix system (3), and is used for controlling the avionic detection system (1) to work and transmitting display signals to the display matrix system (3);
and the control terminal is used for being connected with the joint test control upper computer and transmitting a control instruction to the joint test control upper computer.
5. The avionics integrated control assembly of claim 2, wherein the number of interconnected displays in the display matrix system is 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510827349.7A CN105373023A (en) | 2015-11-24 | 2015-11-24 | Avionics integration test integrated control assembly |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510827349.7A CN105373023A (en) | 2015-11-24 | 2015-11-24 | Avionics integration test integrated control assembly |
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| Publication Number | Publication Date |
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| CN105373023A true CN105373023A (en) | 2016-03-02 |
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| CN201510827349.7A Pending CN105373023A (en) | 2015-11-24 | 2015-11-24 | Avionics integration test integrated control assembly |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107390069A (en) * | 2017-08-17 | 2017-11-24 | 西安北方光电科技防务有限公司 | A kind of fault rapid detecting method and detecting system |
| CN109192037A (en) * | 2018-07-28 | 2019-01-11 | 国营芜湖机械厂 | A kind of avionics joint-trial environmental technology arrangement demo system based on VR |
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| CN201829074U (en) * | 2010-09-28 | 2011-05-11 | 北京赛四达科技股份有限公司 | Avionics simulation testing and training device |
| CN202502407U (en) * | 2012-01-05 | 2012-10-24 | 中国商用飞机有限责任公司 | Avionics equipment testing device |
| CN203012047U (en) * | 2012-11-30 | 2013-06-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Avionics device function test system |
| CN203217366U (en) * | 2013-03-22 | 2013-09-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Simulation excitation and comprehensive testing apparatus for electromechanical non-bus signals and bus signals |
| CN103760439A (en) * | 2013-09-24 | 2014-04-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Automatic test system of avionic system |
| JP2014130607A (en) * | 2014-01-20 | 2014-07-10 | Fuji Mach Mfg Co Ltd | Integrated control device and integrated control method |
| CN204291192U (en) * | 2014-06-16 | 2015-04-22 | 马国光 | A kind of multi-screen splicing processor |
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2015
- 2015-11-24 CN CN201510827349.7A patent/CN105373023A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201829074U (en) * | 2010-09-28 | 2011-05-11 | 北京赛四达科技股份有限公司 | Avionics simulation testing and training device |
| CN202502407U (en) * | 2012-01-05 | 2012-10-24 | 中国商用飞机有限责任公司 | Avionics equipment testing device |
| CN203012047U (en) * | 2012-11-30 | 2013-06-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Avionics device function test system |
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| CN103760439A (en) * | 2013-09-24 | 2014-04-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Automatic test system of avionic system |
| JP2014130607A (en) * | 2014-01-20 | 2014-07-10 | Fuji Mach Mfg Co Ltd | Integrated control device and integrated control method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107390069A (en) * | 2017-08-17 | 2017-11-24 | 西安北方光电科技防务有限公司 | A kind of fault rapid detecting method and detecting system |
| CN107390069B (en) * | 2017-08-17 | 2023-08-04 | 西安北方光电科技防务有限公司 | Rapid fault detection method and system |
| CN109192037A (en) * | 2018-07-28 | 2019-01-11 | 国营芜湖机械厂 | A kind of avionics joint-trial environmental technology arrangement demo system based on VR |
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Application publication date: 20160302 |