CN106292486A - A kind of information processing method of Airborne Inertial navigation system based on double remainings - Google Patents
A kind of information processing method of Airborne Inertial navigation system based on double remainings Download PDFInfo
- Publication number
- CN106292486A CN106292486A CN201610664201.0A CN201610664201A CN106292486A CN 106292486 A CN106292486 A CN 106292486A CN 201610664201 A CN201610664201 A CN 201610664201A CN 106292486 A CN106292486 A CN 106292486A
- Authority
- CN
- China
- Prior art keywords
- inertial navigation
- navigation system
- optical fiber
- laser
- data
- 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
-
- 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
- G05B19/048—Monitoring; Safety
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Navigation (AREA)
- Traffic Control Systems (AREA)
Abstract
The present invention relates to a kind of Airborne Inertial guidance system data using method based on double remainings, double Redundant Inertial Navigation Systems are carried out data validity judgement and selection, described pair of Redundant Inertial Navigation System, by laser-inertial navigation system, optical fiber inertial navigation system, task system, 1553B bus forms, described data using method, arrange including laser-inertial navigation system state and report task system, optical fiber inertial navigation system mode arranges and reports task system, task system is to the judgement of double Redundant Inertial Navigation System data validitys and selection, the display of inertial navigation system running status.Present method solves the most effective problem of selecting to double remaining inertial navigation system navigation datas, provide guarantee for the availability of navigation system in flight course and reliability, for ensureing that the safety of aircraft and pilot has great importance.
Description
Technical field
The invention belongs to airborne equipment system regions, be specifically related to a kind of Airborne Inertial navigation system based on double remainings
Information processing method.
Background technology
Navigator is the eyes of aircraft, most important for the flight safety of aircraft and the safety of pilot, and flies
Depending on member judges to use the navigation information of navigation system mainly to pass through the status information that navigation system self reports, therefore, navigation
Equipment needs in real time, provides the status information of self for pilot's reference to aircraft task system exactly.
Due to requirement and the heavily quantitative limitation of airplane design, an inertial navigation system is the most only installed on aircraft in early days
System, when it breaks down or data are unavailable, can be to task system reporting fault state, and aircraft is the most just without can
Inertial navigation data, the accuracy of aircraft flight, reliability will not ensure, even affect flight safety.
Along with the enhancing of reliability requirement in airplane design, aircraft have employed two inertial navigation systems of double remaining,
The two backups each other, thus improves the reliability of flight.But also bring new problem, when active and standby inertial navigation system is same
Time when having reported self state and data message to task system, task system needs any information source of decision-making final utilization
Data.
Summary of the invention
Present invention aim to address in double Redundant Inertial Navigation Systems, judge navigation system state and selection in real time
The problem of effective navigation data, thus improve accuracy and the reliability of flight navigation.
A kind of information processing method of based on double remainings the Airborne Inertial navigation system of the present invention, described pair of remaining inertia
Navigation system, including laser-inertial navigation system, optical fiber inertial navigation system, task processing system and 1553B bus, described
Double remaining guidance system data processing methods comprise the following steps:
(1) task processing system periodically through 1553 buses receive laser-inertial navigation systems status data information and
Navigation data information, receives status data information and the navigation data information of optical fiber inertial navigation system；Wherein, laser inertia is led
The status information of boat system and optical fiber inertial navigation system all includes the faulty word that navigates；
(2) when the navigation faulty word receiving laser-inertial navigation system is 0 and navigation data effective word is 1, task
Processing system thinks that laser-inertial navigation system is in normal operating conditions, and the navigation data of laser-inertial navigation system is effective
Can use, laser-inertial navigation system is now set and takes boat equipment as the leading factor, and control the navigational parameter on display screen at aircraft
Information page shows the navigation data information from laser-inertial navigation system real-time reception；When receiving laser-inertial navigation system
Navigation faulty word be 1 and time navigation data effective word is 0, task processing system thinks that laser-inertial navigation system is in fault
State, navigation data is invalid, carries out step (3)；
(3) when the navigation faulty word receiving optical fiber inertial navigation system is 0 and navigation data effective word is 1, task
Processing system thinks that optical fiber inertial navigation system is in normal operating conditions, and optical fiber inertial navigation system navigation data is effectively may be used
, optical fiber inertial navigation system is now set and takes boat equipment as the leading factor, and control the navigational parameter letter on display screen at aircraft
The breath page shows the navigation data information from optical fiber inertial navigation system real-time reception；When receiving optical fiber inertial navigation system
When navigation faulty word is 1 and navigation data effective word is 0, task processing system thinks that optical fiber inertial navigation system is in fault shape
State, navigation data is invalid, carries out step (4)；
(4) task processing system controls to show that laser inertia is led on display floater at aircraft with the form of flight failure inventory
Boat system and the fault message of optical fiber inertial navigation system.
A kind of based on double remainings the Airborne Inertial guidance system data usings method that the present invention proposes, solve in double remainings
In inertial navigation system, judge navigation system state in real time and select the problem of effective navigation data, improve flight and lead
The accuracy of boat and reliability, for ensureing that the safety of aircraft flight and pilot has great importance.
Accompanying drawing explanation
Fig. 1 is double Redundant Inertial Navigation System schematic diagrams；
Fig. 2 is the data using method flow chart of double Redundant Inertial Navigation Systems of the present invention.
Detailed description of the invention
With example, the present invention is elaborated below in conjunction with the accompanying drawings.
On aircraft (including fighter plane, helicopter, transporter etc.), great majority are all equipped with a laser-inertial navigation system
With an optical fiber inertial navigation system, laser-inertial navigation system precision is high, but weight is big, cost is high, optical fiber inertial navigation
System cost is low, lightweight, but precision is low, and the two high level matches with low level uses, and substantially increases the reliability of inertial navigation system
With availability.
For aircraft with pilot, for the state of inertial navigation system, they are primarily upon 2 contents: the
One, whether inertial navigation system breaks down；Second, whether high data can be used；And the present invention propose based on
The Airborne Inertial guidance system data using method of double remainings, it is possible to provide safe and reliable navigation information for flight.
A kind of information processing method of Airborne Inertial navigation system based on double remainings, described pair of remaining inertial navigation system
System, including laser-inertial navigation system, optical fiber inertial navigation system, task processing system and 1553B bus, described pair of remaining
Guidance system data processing method comprises the following steps:
(1) task processing system periodically through 1553 buses receive laser-inertial navigation systems status data information and
Navigation data information, receives status data information and the navigation data information of optical fiber inertial navigation system；Wherein, laser inertia is led
The status information of boat system and optical fiber inertial navigation system all includes the faulty word that navigates；
(2) when the navigation faulty word receiving laser-inertial navigation system is 0 and navigation data effective word is 1, task
Processing system thinks that laser-inertial navigation system is in normal operating conditions, and the navigation data of laser-inertial navigation system is effective
Can use, laser-inertial navigation system is now set and takes boat equipment as the leading factor, and control the navigational parameter on display screen at aircraft
Information page shows the navigation data information from laser-inertial navigation system real-time reception；When receiving laser-inertial navigation system
Navigation faulty word be 1 and time navigation data effective word is 0, task processing system thinks that laser-inertial navigation system is in fault
State, navigation data is invalid, carries out step (3)；
(3) when the navigation faulty word receiving optical fiber inertial navigation system is 0 and navigation data effective word is 1, task
Processing system thinks that optical fiber inertial navigation system is in normal operating conditions, and optical fiber inertial navigation system navigation data is effectively may be used
, optical fiber inertial navigation system is now set and takes boat equipment as the leading factor, and control the navigational parameter letter on display screen at aircraft
The breath page shows the navigation data information from optical fiber inertial navigation system real-time reception；When receiving optical fiber inertial navigation system
When navigation faulty word is 1 and navigation data effective word is 0, task processing system thinks that optical fiber inertial navigation system is in fault shape
State, navigation data is invalid, carries out step (4)；
(4) task processing system controls to show that laser inertia is led on display floater at aircraft with the form of flight failure inventory
Boat system and the fault message of optical fiber inertial navigation system.
Claims (1)
1. an information processing method for Airborne Inertial navigation system based on double remainings, described pair of Redundant Inertial Navigation System,
Including laser-inertial navigation system, optical fiber inertial navigation system, task processing system and 1553B bus, described pair of remaining is led
Boat system data processing method comprises the following steps:
(1) task processing system receives status data information and the navigation of laser-inertial navigation system periodically through 1553 buses
Data message, receives status data information and the navigation data information of optical fiber inertial navigation system；Wherein, laser-inertial navigation system
The status information of system and optical fiber inertial navigation system all includes the faulty word that navigates；
(2) when the navigation faulty word receiving laser-inertial navigation system is 0 and navigation data effective word is 1, task processes
System thinks that laser-inertial navigation system is in normal operating conditions, and the navigation data of laser-inertial navigation system is effectively usable
, laser-inertial navigation system is now set and takes boat equipment as the leading factor, and control the navigational parameter information on display screen at aircraft
The page shows the navigation data information from laser-inertial navigation system real-time reception；When receiving leading of laser-inertial navigation system
When boat faulty word is 1 and navigation data effective word is 0, task processing system thinks that laser-inertial navigation system is in fault shape
State, navigation data is invalid, carries out step (3)；
(3) when the navigation faulty word receiving optical fiber inertial navigation system is 0 and navigation data effective word is 1, task processes
System thinks that optical fiber inertial navigation system is in normal operating conditions, and optical fiber inertial navigation system navigation data is effectively usable
, optical fiber inertial navigation system is now set and takes boat equipment as the leading factor, and control the navigational parameter information on display screen at aircraft
The page shows the navigation data information from optical fiber inertial navigation system real-time reception；When receiving leading of optical fiber inertial navigation system
When boat faulty word is 1 and navigation data effective word is 0, task processing system thinks that optical fiber inertial navigation system is in fault shape
State, navigation data is invalid, carries out step (4)；
(4) task processing system controls to show laser-inertial navigation system on display floater at aircraft with the form of flight failure inventory
System and the fault message of optical fiber inertial navigation system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610664201.0A CN106292486A (en) | 2016-08-12 | 2016-08-12 | A kind of information processing method of Airborne Inertial navigation system based on double remainings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610664201.0A CN106292486A (en) | 2016-08-12 | 2016-08-12 | A kind of information processing method of Airborne Inertial navigation system based on double remainings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106292486A true CN106292486A (en) | 2017-01-04 |
Family
ID=57669109
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610664201.0A Pending CN106292486A (en) | 2016-08-12 | 2016-08-12 | A kind of information processing method of Airborne Inertial navigation system based on double remainings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106292486A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1646880A (en) * | 2002-08-01 | 2005-07-27 | 罗伯特-博希股份公司 | Method for monitoring at least one sensor |
| US20050240812A1 (en) * | 2004-04-07 | 2005-10-27 | International Business Machines Corporation | Arbitration method and system for redundant controllers, with output interlock and automatic switching capabilities |
| CN202339354U (en) * | 2011-11-29 | 2012-07-18 | 福建物联天下信息科技有限公司 | Spatial motion sensor |
| CN104180803A (en) * | 2014-09-09 | 2014-12-03 | 北京航空航天大学 | Non-similar dual-redundancy integrated navigation device applied to unmanned plane |
| CN105527506A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Intelligent fault message detection system and transmission method thereof |
| CN105698788A (en) * | 2014-10-09 | 2016-06-22 | 霍尼韦尔国际公司 | Systems and methods for producing two independent dissimilar attitude solutions, two independent dissimilar inertial solutions or both from one improved navigation device |
-
2016
- 2016-08-12 CN CN201610664201.0A patent/CN106292486A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1646880A (en) * | 2002-08-01 | 2005-07-27 | 罗伯特-博希股份公司 | Method for monitoring at least one sensor |
| US20050240812A1 (en) * | 2004-04-07 | 2005-10-27 | International Business Machines Corporation | Arbitration method and system for redundant controllers, with output interlock and automatic switching capabilities |
| CN202339354U (en) * | 2011-11-29 | 2012-07-18 | 福建物联天下信息科技有限公司 | Spatial motion sensor |
| CN104180803A (en) * | 2014-09-09 | 2014-12-03 | 北京航空航天大学 | Non-similar dual-redundancy integrated navigation device applied to unmanned plane |
| CN105527506A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Intelligent fault message detection system and transmission method thereof |
| CN105698788A (en) * | 2014-10-09 | 2016-06-22 | 霍尼韦尔国际公司 | Systems and methods for producing two independent dissimilar attitude solutions, two independent dissimilar inertial solutions or both from one improved navigation device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9613536B1 (en) | Distributed flight management system | |
| CN104108466B (en) | Flight System For An Aircraft Having An Autoland System | |
| EP2795416A1 (en) | Safe takeoff monitoring system | |
| CN115390432B (en) | Redundancy unmanned aerial vehicle flight control system and flight control method | |
| CN112650279A (en) | Cloud flight management system and cloud flight management method for airplane | |
| Skoog et al. | Leveraging astm industry standard f3269-17 for providing safe operations of a highly autonomous aircraft | |
| Young et al. | Flight simulation study of airplane state awareness and prediction technologies | |
| CN106546258B (en) | A kind of inertial navigation system state reporting method based on double redundancy | |
| CN112286220A (en) | System and method for autonomously monitoring highly automated vehicle operation | |
| Spielman et al. | Boeing 737 MAX: Expectation of human capability in highly automated systems | |
| Kramer et al. | Quantifying pilot contribution to flight safety during hydraulic systems failure | |
| CN107316087B (en) | Method for judging fault use of aviation product | |
| CN106292486A (en) | A kind of information processing method of Airborne Inertial navigation system based on double remainings | |
| Johnson | The hidden human factors in unmanned aerial vehicles | |
| Miltner et al. | Modeling and utilization of synthetic data for improved automation and human-machine interface continuity | |
| Etherington et al. | Quantifying pilot contribution to flight safety during dual generator failure | |
| CN109844845A (en) | Automatic armed of the aircraft wide-angle into nearly function | |
| Ellis et al. | Design considerations for attitude state awareness and prevention of entry into unusual attitudes | |
| Greenwell et al. | What should aviation safety incidents teach us | |
| Duan et al. | A multiple hypothesis prediction method for improved aircraft state awareness | |
| Smaili et al. | Conceptual Design and Evaluation of Upset-Recovery Systems for Civil Transport Aircraft | |
| Evjemo et al. | Lessons learned from increased automation in aviation: The paradox related to the high degree of safety and implications for future research | |
| US20230229992A1 (en) | System for vehicle operator workload assessment and annunciation | |
| Sherry et al. | Anatomy of a No-Equipment-Failed (NEF) ICNS System Malfunction: The Case of Singapore Airlines SQ-327 Runway Excursion | |
| US20130325216A1 (en) | System and method for authorizing stoppage of piloting tasks |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170104 |
|
| WD01 | Invention patent application deemed withdrawn after publication |