CN109870997A - A kind of triplex redundance flight control computer system - Google Patents
A kind of triplex redundance flight control computer system Download PDFInfo
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- CN109870997A CN109870997A CN201711259883.8A CN201711259883A CN109870997A CN 109870997 A CN109870997 A CN 109870997A CN 201711259883 A CN201711259883 A CN 201711259883A CN 109870997 A CN109870997 A CN 109870997A
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Abstract
The present invention relates to a kind of triplex redundance flight control computer systems, comprising: system management module, redundancy management module, Flight Control Software, data I/O module and operating system module；The system management module includes starting module, task scheduling unit and task executing units；The redundancy management module includes synchronization module, Cross talk unit, compares monitoring module and fault comprehensive module；The Flight Control Software includes instruction process unit, control law reconstruction unit and control law computer unit；The data I/O module includes device driver module, serial data collection unit, A/D data acquisition unit and D/A output unit；The operating system module includes WDB debugging unit, Integrated Development Environment unit and vxworks operating system；Triplex redundance flight control computer system of the invention rationally, properly and securely, satisfies the use demand.Entire flight control system also meets the design objective of failure safe twice.
Description
Technical field
The present invention relates to flight control system technical field more particularly to a kind of triplex redundance flight control computer systems.
Background technique
With the development of unmanned plane the relevant technologies, unmanned plane all has wide practical use in military and civilian field.?
Military aspect, unmanned plane can be used as aerial reconnaissance and weapon platform, execute scouting by carrying different equipment and equipment, empty
War, air-to-ground attack, electronic interferences, target positioning, the tasks such as recruitment evaluation.At civilian aspect, unmanned plane can be used for carrying out map
Mapping, air communication, rain making, meteorological detection, forest survey, atmosphere and ocean are taken a sample to research.In recent years, with various
The development of aviation and electronic technology, the development for making unmanned plane be advanced by leaps and bounds in performance.With unmanned plane during flying function
Increasing, mission requirements become increasingly complex, and make becoming increasingly complex for flight control system change, so that the frequency that breaks down will be more
Come higher.
With the development of super large-scale integration and advancing by leaps and bounds for electronic technology, many people think that flight control computer can
By property oneself through very high, do not have to consider that its is ineffectiveness, if but flight control computer once break down, very likely fall
Machine event causes very big loss.Studies in China has the comparison of man-machine reliability more, such as China ACT verification machine digital FBW
Flight control system takes the architecture of four remainings, greatly improves the reliability of flight control system, and China is at nobody
Research in terms of the reliability of machine compares less, and technical aspect also compares lag.
Summary of the invention
The purpose of the present invention is what is be achieved through the following technical solutions.
A kind of triplex redundance flight control computer system, comprising: control centre, system management module, redundancy management module, flight
Control software, data I/O module and operating system module；The control centre respectively with system management module, redundancy management mould
Block, Flight Control Software, data I/O module are connected with operating system module；The system management module includes starting module, appoints
Business scheduling unit and task executing units；The redundancy management module includes synchronization module, Cross talk unit, compares monitoring mould
Block and fault comprehensive module；The Flight Control Software includes that instruction process unit, control law reconstruction unit and control law calculate
Machine unit；The data I/O module include device driver module, serial data collection unit, A/D data acquisition unit and
D/A output unit；The operating system module includes WDB debugging unit, Integrated Development Environment unit and VxWorks operation system
System.
Further, the starting module in system management module includes: software initialization unit and hardware initialization unit.
Further, the synchronization module in redundancy management module includes: synchronous recovery unit and synchronous averaging unit；It is described
Comparing monitoring module includes: input comparing unit and output comparing unit；The fault comprehensive module includes: fault comprehensive unit
With failure logging unit.
Further, the device driver module in data IO software includes: clock interrupt driver unit, A/D
Driving unit and D/A driving unit.
The present invention has the advantages that triplex redundance flight control computer system of the invention is rationally, properly and securely, meets and use
Demand.Entire flight control system also meets the design objective of failure safe twice.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
It obtains other drawings based on these drawings.
Attached drawing 1 shows a kind of triplex redundance flight control computer system of embodiment according to the present invention.
Specific embodiment
In the following detailed description, many details are proposed, in order to complete understanding of the present invention.But
It will be apparent to those skilled in the art that the present invention can not need some details in these details
In the case of implement.Below to the description of embodiment just for the sake of provided by showing example of the invention to it is of the invention more
Understand well.
Below in conjunction with attached drawing, the technical solution of the embodiment of the present invention is described.
As shown in Figure 1, the present invention provides a kind of triplex redundance flight control computer system, comprising: control centre, system administration mould
Block, redundancy management module, Flight Control Software, data I/O module and operating system module；The control centre respectively with system
Management module, redundancy management module, Flight Control Software, data I/O module are connected with operating system module；The system administration
Module includes starting module, task scheduling unit and task executing units；The redundancy management module includes synchronization module, intersects
Communication unit compares monitoring module and fault comprehensive module；The Flight Control Software includes instruction process unit, control law weight
Structure unit and control law computer unit；The data I/O module include device driver module, serial data collection unit,
A/D data acquisition unit and D/A output unit；The operating system module includes WDB debugging unit, Integrated Development Environment unit
And vxworks operating system.
According to an aspect of the present invention, the starting module in system management module includes: software initialization unit and hard
Part initialization unit.
According to an aspect of the present invention, the synchronization module in redundancy management module include: synchronous recovery unit with it is synchronous
Start unit；The relatively monitoring module includes: input comparing unit and output comparing unit；The fault comprehensive module packet
It includes: fault comprehensive unit and failure logging unit.
According to an aspect of the present invention, the device driver module in data IO software includes: clock interrupt driving
Program unit, A/D driving unit and D/A driving unit.
Triplex redundance flight control computer system of the invention rationally, properly and securely, satisfies the use demand.Entire flight control
System also meets the design objective of failure safe twice.
The present invention is not limited to examples detailed above, in claims of the present invention limited range, art technology
The various deformations or amendments that personnel can make without creative work are protected by this patent.
Claims (4)
1. a kind of triplex redundance flight control computer system characterized by comprising control centre, system management module, redundancy management
Module, Flight Control Software, data I/O module and operating system module；The control centre respectively with system management module, remaining
Degree management module, Flight Control Software, data I/O module are connected with operating system module；The system management module includes starting
Module, task scheduling unit and task executing units；The redundancy management module includes synchronization module, Cross talk unit, ratio
Compared with monitoring module and fault comprehensive module；The Flight Control Software includes instruction process unit, control law reconstruction unit and control
System rule computer unit；The data I/O module includes that device driver module, serial data collection unit, A/D data are adopted
Collect unit and D/A output unit；The operating system module includes WDB debugging unit, Integrated Development Environment unit and VxWorks
Operating system.
2. a kind of triplex redundance flight control computer system according to claim 1, which is characterized in that the system management module
In starting module include: software initialization unit and hardware initialization unit.
3. a kind of triplex redundance flight control computer system according to claim 1, which is characterized in that the redundancy management module
In synchronization module include: synchronous recovery unit and synchronous averaging unit；The relatively monitoring module includes: input comparing unit
With output comparing unit；The fault comprehensive module includes: fault comprehensive unit and failure logging unit.
4. a kind of triplex redundance flight control computer system according to claim 1, which is characterized in that in the data IO software
Device driver module include: clock interrupt driver unit, A/D driving unit and D/A driving unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711259883.8A CN109870997A (en) | 2017-12-04 | 2017-12-04 | A kind of triplex redundance flight control computer system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711259883.8A CN109870997A (en) | 2017-12-04 | 2017-12-04 | A kind of triplex redundance flight control computer system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109870997A true CN109870997A (en) | 2019-06-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711259883.8A Pending CN109870997A (en) | 2017-12-04 | 2017-12-04 | A kind of triplex redundance flight control computer system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112540918A (en) * | 2020-12-04 | 2021-03-23 | 中国航空工业集团公司成都飞机设计研究所 | Redundancy flight pipe computer synchronous debugging method based on ARINC659 bus |
| CN113377005A (en) * | 2021-05-31 | 2021-09-10 | 四川腾盾科技有限公司 | Air management and control method, system, computer program and storage medium of redundancy airplane management computer software |
-
2017
- 2017-12-04 CN CN201711259883.8A patent/CN109870997A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112540918A (en) * | 2020-12-04 | 2021-03-23 | 中国航空工业集团公司成都飞机设计研究所 | Redundancy flight pipe computer synchronous debugging method based on ARINC659 bus |
| CN113377005A (en) * | 2021-05-31 | 2021-09-10 | 四川腾盾科技有限公司 | Air management and control method, system, computer program and storage medium of redundancy airplane management computer software |
| CN113377005B (en) * | 2021-05-31 | 2022-09-16 | 四川腾盾科技有限公司 | Air management and control method, system and storage medium for redundancy airplane management computer software |
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Application publication date: 20190611 |