CN104238529A - Integral processing unit architecture of highly-integrated flight environment monitoring system - Google Patents
Integral processing unit architecture of highly-integrated flight environment monitoring system Download PDFInfo
- Publication number
- CN104238529A CN104238529A CN201410512735.2A CN201410512735A CN104238529A CN 104238529 A CN104238529 A CN 104238529A CN 201410512735 A CN201410512735 A CN 201410512735A CN 104238529 A CN104238529 A CN 104238529A
- Authority
- CN
- China
- Prior art keywords
- information
- master cpu
- interface
- end processing
- air traffic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
Abstract
The invention provides an integral processing unit architecture of a highly-integrated flight environment monitoring system. In terms of hardware, a master control CPU (central processing unit) component plus a signal processing component are adopted to form a hardware architecture; the signal processing component comprises an air-traffic front-end processing module and a weather-radar front-end processing module. The integral processing unit architecture solves the problems of large size of existing march-type systems, incapability of high information integration and low software-hardware resource sharing performance, and has high practical value.
Description
Technical field
The invention belongs to the communication/identification/surveillance technology field of aviation electronics task, be specifically related to a kind of high integrity flight environment of vehicle surveillance overall treatment unit structure, it carries out comprehensive integration design to each module in flight environment of vehicle surveillance, share software and hardware resources, the number of minimizing equipment and the weight of equipment, improve system reliability.
Background technology
The flight environment of vehicle surveillance comprehensive integration systemic-function such as enhancement mode ground proximity warning system (EGPWS), air traffic early warning and collision avoidance system (TCAS/S) and weather radar/forward sight wind shear detection system (Weather Radar/PWS).For pilot provides about the regarding safety information such as meteorology, air traffic situation, landform, strengthen pilot to the environmental situation perception degree around aircraft and adaptability to changes, effectively the generation of all kinds of aircraft accident of prevention, improves flight safety greatly.Current flight environment of vehicle surveillance adopts the autonomous system of march-past or association type mostly, and the technology of march-past framework and manufacturing process are comparatively ripe, but this type of framework exists many drawbacks: one is that warning right of priority and Heterogeneous Information management are limited; Two is that between subsystem, interactivity is poor; Three is that control panel is many repeats with function; Four is that mounting process is complicated; Five is that weight is large, volume is large, power consumption is high and maintenance task is heavy.Some flight environment of vehicle surveillance is the TCAS+WXR association type system (part is comprehensive) based on ARINC429/453, this system current only accomplishes that part software and hardware resources is shared, just modular design is carried out to each ripe subsystem, reach certain comprehensive, relative march-past system is optimized to some extent, but it is more that it still exists occupying system resources, the defect that weight, volume, power consumption are larger, is therefore necessary to propose to improve.
Summary of the invention
The technical matters that the present invention solves: provide a kind of high integrity flight environment of vehicle surveillance overall treatment unit structure, solves that existing march-past system bulk is large, information can not high integrity, problem that software and hardware resources sharing degree is not high.
The technical solution used in the present invention: high integrity flight environment of vehicle surveillance overall treatment unit structure, has master cpu assembly and signal processing component;
Described master cpu assembly comprises master cpu, speech interface, AFDX communication interface and ARINC429 communication interface and discrete magnitude I/O interface;
Described signal processing component comprises air traffic front end processing block and meteorological radar front end processing module;
Described speech interface produces 8 Ω 4W, 600 Ω 400mW two-way alarm voice, is sent to airborne voice system and realizes system audible and visual alarm;
The airborne information that described AFDX communication interface receives inertial reference system by AFDX bus, air data computer, radio altimeter, flight management system, GPS resolve and control information; Send display and flight management system on Distal promoter, meteorological display information and warning information to machine;
Described ARINC429 communication interface carries maintenance information by ARINC429 bus receiver and sends air traffic display information and maintenance information;
Described discrete magnitude I/O interface undercarriage, sky/ground state, flap configuration information send suppression information and control panel control information;
The radiofrequency signal of outside TCAS and S mode answering machine is passed through process by described air traffic front end processing block, encoding and decoding send master cpu assembly to, the distance and bearing information that the weather radar cell signal received is carried out demodulation acquisition relevant by described weather radar front end processing block sends master cpu assembly to through coding, described master cpu assembly receiver information carrying breath, with the coded message received from signal processing component through information fusion and algorithm computing, produce enhancement mode Distal promoter, air traffic, meteorological warning information and video information deliver to airborne display system and acousto-optic warning system,
Above-mentioned interface and the crosslinked of master cpu are realized by FPGA, described FPGA is used as signaling interface conversion and bus extension, the different pieces of information bus type of each interface is converted to the exchanges data that cpci bus that master cpu can use realizes master cpu and above-mentioned interface.
The present invention compared with prior art reduces weight, volume, power, amount of parts and cable amount needed for function for monitoring equipment, improves system reliability, has saved system resource.
Accompanying drawing explanation
Fig. 1 is hardware structure theory diagram of the present invention;
Fig. 2 is software architecture theory diagram of the present invention.
Embodiment
Below in conjunction with accompanying drawing 1,2, a kind of embodiment of the present invention is described.
High integrity flight environment of vehicle surveillance overall treatment unit structure, hardware aspect adopts master cpu assembly+signal processing component to complete hardware structure, and signal processing component is divided into air traffic front end processing block and meteorological radar front end processing module.Air traffic front end processing block sends the radiofrequency signal of outside TCAS and S mode answering machine to master cpu assembly by process, encoding and decoding etc.The weather radar cell signal received is carried out demodulation and is obtained relevant distance and bearing information by weather radar front end processing block, sends master cpu assembly to through coding.Master cpu assembly receiver information carrying ceases, with the coded message received from signal processing component through information fusion, by special algorithm computing, the warning information such as generation enhancement mode Distal promoter, air traffic, meteorology and video information deliver to airborne display system and acousto-optic warning system.
Software aspect adopts embedded vxworks operating system, use real-time multi-task processing mode, each function carries out independent task process, ensure that the running status of different functional modules does not interfere with each other, these software systems, by among the Function Integration Mechanism of Distal promoter, air traffic and weather radar back-end processing to an independent system, make this system can realize integrated supervision function.
Above-mentioned master cpu adopts PowerPC85xx (or 86xx), and the airborne information that master cpu will receive, is distributed to the air traffic front end processing block in signal processing component and meteorological radar front end processing module; The monitor message of the air traffic front end processing block received and meteorological radar front end processing module is carried out comprehensively, achieves the management of informix that flight environment of vehicle monitors, data fusion, the management of warning voice, airborne message exchange and each module.
Described master cpu assembly comprises master cpu, speech interface, AFDX communication interface and ARINC429 communication interface and discrete magnitude I/O interface;
Described signal processing component comprises air traffic front end processing block and meteorological radar front end processing module;
Described speech interface produces 8 Ω 4W, 600 Ω 400mW two-way alarm voice, is sent to airborne voice system and realizes system audible and visual alarm;
The airborne information that described AFDX communication interface receives inertial reference system by AFDX bus, air data computer, radio altimeter, flight management system, GPS resolve and control information; Send display and flight management system on Distal promoter, meteorological display information and warning information to machine;
Described ARINC429 communication interface carries maintenance information by ARINC429 bus receiver and sends air traffic display information and maintenance information;
Described discrete magnitude I/O interface undercarriage, sky/ground state, flap configuration information send suppression information and control panel control information;
The radiofrequency signal of outside TCAS and S mode answering machine is passed through process by described air traffic front end processing block, encoding and decoding send master cpu assembly to, the distance and bearing information that the weather radar cell signal received is carried out demodulation acquisition relevant by described weather radar front end processing block sends master cpu assembly to through coding, described master cpu assembly receiver information carrying breath, with the coded message received from signal processing component through information fusion and algorithm computing, produce enhancement mode Distal promoter, air traffic, meteorological warning information and video information deliver to airborne display system and acousto-optic warning system,
Above-mentioned interface and the crosslinked of master cpu are realized by FPGA, described FPGA is used as signaling interface conversion and bus extension, the different pieces of information bus type of each interface is converted to the exchanges data that cpci bus that master cpu can use realizes master cpu and above-mentioned interface.
Software section is made up of 6 tasks, and the function of these tasks is as follows:
A) airborne information transmit-receive task: recipient processor information carrying breath (the airborne information such as orientation, course, Shi Ji, by ARINC429 interface, the input and output of AFDX interface, also has the input of discrete magnitude interface);
B) informix Processing tasks: the information such as comprehensive air traffic, meteorology, landform, produces the information such as alarm, display;
C) warning information Processing tasks: produce sound signal, audio frequency warning information being delivered to airborne equipment exports;
D) weather radar information handling task: generate meteorological and warning information;
E) air traffic information Processing tasks: generate air traffic Anticollision information;
F) Distal promoter information handling task: generate landform and warning information;
G) task is shown: the display information such as landform, traffic, meteorology that generate deliver to airborne display devices.
Above-described embodiment, just preferred embodiment of the present invention, is not used for limiting the scope of the present invention, therefore all equivalence changes done with content described in the claims in the present invention, all should be included within the claims in the present invention scope.
Claims (1)
1. high integrity flight environment of vehicle surveillance overall treatment unit structure, is characterized in that having master cpu assembly and signal processing component;
Described master cpu assembly comprises master cpu, speech interface, AFDX communication interface and ARINC429 communication interface and discrete magnitude I/O interface;
Described signal processing component comprises air traffic front end processing block and meteorological radar front end processing module;
Described speech interface produces 8 Ω 4W, 600 Ω 400mW two-way alarm voice, is sent to airborne voice system and realizes system audible and visual alarm;
The airborne information that described AFDX communication interface receives inertial reference system by AFDX bus, air data computer, radio altimeter, flight management system, GPS resolve and control information; Send display and flight management system on Distal promoter, meteorological display information and warning information to machine;
Described ARINC429 communication interface carries maintenance information by ARINC429 bus receiver and sends air traffic display information and maintenance information;
Described discrete magnitude I/O interface undercarriage, sky/ground state, flap configuration information send suppression information and control panel control information;
The radiofrequency signal of outside TCAS and S mode answering machine is passed through process by described air traffic front end processing block, encoding and decoding send master cpu assembly to, the distance and bearing information that the weather radar cell signal received is carried out demodulation acquisition relevant by described weather radar front end processing block sends master cpu assembly to through coding, described master cpu assembly receiver information carrying breath, with the coded message received from signal processing component through information fusion and algorithm computing, produce enhancement mode Distal promoter, air traffic, meteorological warning information and video information deliver to airborne display system and acousto-optic warning system,
Above-mentioned interface and the crosslinked of master cpu are realized by FPGA, described FPGA is used as signaling interface conversion and bus extension, the different pieces of information bus type of each interface is converted to the exchanges data that cpci bus that master cpu can use realizes master cpu and above-mentioned interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410512735.2A CN104238529A (en) | 2014-09-29 | 2014-09-29 | Integral processing unit architecture of highly-integrated flight environment monitoring system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410512735.2A CN104238529A (en) | 2014-09-29 | 2014-09-29 | Integral processing unit architecture of highly-integrated flight environment monitoring system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104238529A true CN104238529A (en) | 2014-12-24 |
Family
ID=52226825
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410512735.2A Pending CN104238529A (en) | 2014-09-29 | 2014-09-29 | Integral processing unit architecture of highly-integrated flight environment monitoring system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104238529A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108877300A (en) * | 2018-06-28 | 2018-11-23 | 中国直升机设计研究所 | A kind of air traffic alarm and collision avoidance system based on FACE framework |
| CN109709629A (en) * | 2018-12-29 | 2019-05-03 | 陕西宝成航空仪表有限责任公司 | Integrated display system for flight environment of vehicle |
| CN110525671A (en) * | 2019-07-17 | 2019-12-03 | 陕西千山航空电子有限责任公司 | A kind of Aero Integrated Alarm System based on AFDX network |
| CN113382374A (en) * | 2021-06-11 | 2021-09-10 | 中国商用飞机有限责任公司 | Unit alarm information full-transmission coding method and device |
-
2014
- 2014-09-29 CN CN201410512735.2A patent/CN104238529A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108877300A (en) * | 2018-06-28 | 2018-11-23 | 中国直升机设计研究所 | A kind of air traffic alarm and collision avoidance system based on FACE framework |
| CN108877300B (en) * | 2018-06-28 | 2021-03-23 | 中国直升机设计研究所 | Air traffic warning and anti-collision system based on FACE framework |
| CN109709629A (en) * | 2018-12-29 | 2019-05-03 | 陕西宝成航空仪表有限责任公司 | Integrated display system for flight environment of vehicle |
| CN110525671A (en) * | 2019-07-17 | 2019-12-03 | 陕西千山航空电子有限责任公司 | A kind of Aero Integrated Alarm System based on AFDX network |
| CN113382374A (en) * | 2021-06-11 | 2021-09-10 | 中国商用飞机有限责任公司 | Unit alarm information full-transmission coding method and device |
| CN113382374B (en) * | 2021-06-11 | 2023-02-07 | 中国商用飞机有限责任公司 | Unit alarm information full-transmission coding method and device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103617750B (en) | Hybrid monitoring collision avoidance warning method and system for multiplex omni-directional antennas | |
| US10451743B2 (en) | Integrated interface architecture and control logic for enhanced emergency location functionality | |
| CN105539867A (en) | Utility aircraft airborne electronic system based on unified processing platform | |
| CN102916778B (en) | A kind of airborne equipment signal processing method and system | |
| CN104238529A (en) | Integral processing unit architecture of highly-integrated flight environment monitoring system | |
| US8892349B2 (en) | Aviation advisory | |
| CN103413465A (en) | Airborne collision avoidance and ground proximity warning monitoring system and monitoring method thereof | |
| CN205334236U (en) | Real -time safety monitoring system of many rotor unmanned aerial vehicle based on beidou system | |
| CN107808551A (en) | A kind of General Aviation operation monitoring system and its monitoring method based on the Big Dipper | |
| US10071819B2 (en) | Systems and methods for providing emergency location functionality | |
| US10170009B2 (en) | Method for transmitting flight parameters of a lead aircraft to an intruder aircraft | |
| US10450084B2 (en) | Emergency locator transmitter activation device for enhanced emergency location performance | |
| CN107403563A (en) | Open the navigation or air flight absolutely empty supervision equipment, method, system and all purpose aircraft | |
| CN105372722B (en) | A kind of spatial domain Wind measurement method and its device | |
| CN113401148A (en) | Control system of unmanned automobile and unmanned automobile | |
| CN102594372B (en) | Software-radio-based intelligent bridge system for ship | |
| CN205959431U (en) | General aviation is monitoring devices, system and general aviation ware air to air | |
| CN104501828A (en) | General aviation onboard monitoring system | |
| CN116884277A (en) | Configurable low-altitude environment sensing and anti-collision system design method | |
| US20120133545A1 (en) | Collision avoidance transponder for aerial hazards and method for reducing collisions with aerial hazards | |
| US10140877B2 (en) | Collision avoidance systems | |
| US9030348B2 (en) | Systems and methods for providing diversity-distance-measuring equipment | |
| CA3007560A1 (en) | Autonomous distress tracking device | |
| CN204287972U (en) | With wireless acoustics function unmanned vehicle | |
| CN112702660A (en) | Multimedia data transmission method and device, automatic driving vehicle and cloud server |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20141224 |