CN101916111A - Electric drive flight control system structure - Google Patents
Electric drive flight control system structure Download PDFInfo
- Publication number
- CN101916111A CN101916111A CN 201010260070 CN201010260070A CN101916111A CN 101916111 A CN101916111 A CN 101916111A CN 201010260070 CN201010260070 CN 201010260070 CN 201010260070 A CN201010260070 A CN 201010260070A CN 101916111 A CN101916111 A CN 101916111A
- Authority
- CN
- China
- Prior art keywords
- flight control
- digital
- control system
- active
- defcs
- 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
Images
Landscapes
- Control By Computers (AREA)
Abstract
The invention belongs to the technology of flight control and relates to the improvement of an electric drive flight control system structure. The structure consists of a flight control computer [1], a command sensor [6], a feedback transducer [7], a discrete switch [8] and a steering engine [9], wherein the flight control computer [1] consists of a signal conditioning circuit [4], a DFCS main digital flight control system [2] and a digital servo controller [5]; and the digital servo controller [5] comprises a servo amplifier [10] and an active/standby transfer switch [11]. The electric drive flight control system structure is characterized in that: a DEFCS digital emergency backup flight control module [12] is arranged inside the digital servo controller [5]; a signal output end of the signal conditioning circuit [4] is connected with an input end of the DEFCS digital emergency backup flight control module [12]; and an output end of the DEFCS digital emergency backup flight control module [12] is connected with a normally open contact of the active/standby transfer switch [11]. The electric drive flight control system structure has the advantages of simple structure, small volume, low cost, convenience debugging and high reliability.
Description
Technical field
The invention belongs to flight control technology, relate to improvement electric drive flight control system structure.
Background technology
The electric drive flight control system structure of the previous passage of order is referring to Fig. 1, and it is made up of flight-control computer 1, instruction sensor 6, feedback transducer 7, discrete switch 8 and steering wheel 9 it.Flight-control computer 1 is made up of signal conditioning circuit 4, DFCS master's digital flight control system 2, AEFCS simulation emergent backup flight control module 3 and digital servo controller 5.Digital servo controller 5 is made up of servoamplifier 10 and active/standby change-over switch 11.Instruction sensor 6, the signal output part of feedback transducer 7 and discrete switch 8 is connected with the respective input of signal conditioning circuit 4 respectively, the signal output part of signal conditioning circuit 4 is connected with the signal input part of DFCS master's digital flight control system 2 with the emergent backup of AEFCS simulation flight control module 3 respectively, active/standby change-over switch 11 is single-pole double-throw switch (SPDT)s, the signal output part of DFCS master's digital flight control system 2 is connected with the normally closed contact of active/standby change-over switch 11, the signal output part of the emergent backup of AEFCS simulation flight control module 3 is connected with the normally opened contact of active/standby change-over switch 11, the common port of active/standby change-over switch 11 is connected with the input end of servoamplifier 10, and the output terminal of servoamplifier 10 is connected with steering wheel 9.The principle of work of said structure is: under the normal condition, after signal conditioning circuit 4 is nursed one's health, import 3 pairs of above-mentioned signals of DFCS master's digital flight control system 2 and AEFCS simulation emergent backup flight control module simultaneously from the signal of instruction sensor 6, feedback transducer 7 and discrete switch 8 and resolve processing, obtain the steering wheel control signal.But the output of the emergent backup of AEFCS simulation flight control module 3 is disconnected, and DFCS master's digital flight control system 2 is controlled steering wheel work through active/standby change-over switch 11 output steering wheel control signals to servoamplifier.When DFCS master's digital flight control system 2 breaks down, can the active/standby change-over switch 11 of manual control carry out active/standby switching; Also can carry out active/standby switching automatically.When needs carried out active/standby switching automatically, the signal input end of active/standby change-over switch 11 was connected with the active/standby change-over switch control signal output ends of DFCS master's digital flight control system 2.When the active/standby change-over switch control signal output ends of DFCS master's digital flight control system 2 was exported active/standby switching signal, active/standby change-over switch 11 was carried out active/standby switching.Under emergent back-up job state, the emergent backup of AEFCS simulation flight control module 3 output steering wheel control signals are to the work of servoamplifier control steering wheel.Its shortcoming is: the emergent backup of AEFCS simulation flight control module 3 is to use hard-wired mimic channel, complex structure, and volume is big, the cost height, debugging work load is big, and reliability is low.
Summary of the invention
The objective of the invention is: propose a kind of simple in structure, volume is little, cost is low, be convenient to debug, electric drive flight control system structure that reliability is high.
Technical scheme of the present invention is: a kind of electric drive flight control system structure, it is made up of flight-control computer 1, instruction sensor 6, feedback transducer 7, discrete switch 8 and steering wheel 9, flight-control computer 1 is made up of signal conditioning circuit 4, DFCS master's digital flight control system 2 and digital servo controller 5, and digital servo controller 5 comprises servoamplifier 10 and active/standby change-over switch 11; The signal output part of instruction sensor 6, feedback transducer 7 and discrete switch 8 is connected with the respective input of signal conditioning circuit 4 respectively, the signal output part of signal conditioning circuit 4 is connected with the signal input part of DFCS master's digital flight control system 2, active/standby change-over switch 11 is single-pole double-throw switch (SPDT)s, the signal output part of DFCS master's digital flight control system 2 is connected with the normally closed contact of active/standby change-over switch 11, the common port of active/standby change-over switch 11 is connected with the input end of servoamplifier 10, and the output terminal of servoamplifier 10 is connected with steering wheel 9; It is characterized in that, the emergent backup of a DEFCS numeral flight control module 12 is arranged in the said digital servo controller 5, in the emergent backup of DEFCS numeral flight control module 12, store emergent backup control law program, the signal output part of signal conditioning circuit 4 is connected with the input end of the emergent backup of DEFCS numeral flight control module 12, and the output terminal of the emergent backup of DEFCS numeral flight control module 12 is connected with the normally opened contact of active/standby change-over switch 11.
Advantage of the present invention is: simple in structure, volume is little, and cost is low, is convenient to debugging, the reliability height.One embodiment of the present of invention, volume have reduced more than 10%, and cost has descended more than 10%.
Description of drawings
Fig. 1 is the electric drive flight control system structure block diagram of an existing passage.
Fig. 2 is a system architecture diagram of the present invention.
Embodiment
Below the present invention is described in further details.Referring to Fig. 2, a kind of electric drive flight control system structure, it is made up of flight-control computer 1, instruction sensor 6, feedback transducer 7, discrete switch 8 and steering wheel 9, flight-control computer 1 is made up of signal conditioning circuit 4, DFCS master's digital flight control system 2 and digital servo controller 5, and digital servo controller 5 comprises servoamplifier 10 and active/standby change-over switch 11; The signal output part of instruction sensor 6, feedback transducer 7 and discrete switch 8 is connected with the respective input of signal conditioning circuit 4 respectively, the signal output part of signal conditioning circuit 4 is connected with the signal input part of DFCS master's digital flight control system 2, active/standby change-over switch 11 is single-pole double-throw switch (SPDT)s, the signal output part of DFCS master's digital flight control system 2 is connected with the normally closed contact of active/standby change-over switch 11, the common port of active/standby change-over switch 11 is connected with the input end of servoamplifier 10, and the output terminal of servoamplifier 10 is connected with steering wheel 9; It is characterized in that, the emergent backup of a DEFCS numeral flight control module 12 is arranged in the said digital servo controller 5, store emergent backup control law program in the emergent backup of the DEFCS numeral flight control module 12, the signal output part of signal conditioning circuit 4 is connected with the input end of the emergent backup of DEFCS numeral flight control module 12, and the output terminal of the emergent backup of DEFCS numeral flight control module 12 is connected with the normally opened contact of active/standby change-over switch 11.
Principle of work of the present invention is: cancelled the emergent backup of AEFCS simulation flight control module 3, in digital servo controller 5, increase and designed the emergent backup of DEFCS numeral flight control module 12, the output of signal conditioning circuit 4 from instruction sensor 6, feedback transducer 7, the emergent backup of DEFCS numeral flight control module 12 in the direct input digit servo controller 5 of the signal of discrete switch 8, when active/standby change-over switch 11 is transformed into emergent Status of Backups, resolve and export the steering wheel control signal by the emergent backup control law in the emergent backup of the DEFCS numeral flight control module 12.The emergent backup of DEFCS numeral flight control module 12 can be made up of hardware or software.In one embodiment of the invention, the function that the emergent backup of AEFCS simulation flight control module 3 need be realized is stored among the CPU of digital servo controller 5 with the form of software.
Claims (1)
1. electric drive flight control system structure, it is made up of flight control computer [1], instruction sensor [6], feedback transducer [7], discrete switch [8] and steering wheel [9], flight-control computer [1] is made up of signal conditioning circuit [4], DFCS master's digital flight control system [2] and digital servo controller [5], and digital servo controller [5] comprises servoamplifier [10] and active/standby change-over switch [11]; Instruction sensor [6], the signal output part of feedback transducer [7] and discrete switch [8] is connected with the respective input of signal conditioning circuit [4] respectively, the signal output part of signal conditioning circuit [4] is connected with the signal input part of DFCS master's digital flight control system [2], active/standby change-over switch [11] is a single-pole double-throw switch (SPDT), the signal output part of DFCS master's digital flight control system [2] is connected with the normally closed contact of active/standby change-over switch [11], the common port of active/standby change-over switch [11] is connected with the input end of servoamplifier [10], and the output terminal of servoamplifier [10] is connected with steering wheel [9]; It is characterized in that, the emergent backup of a DEFCS numeral flight control module [12] is arranged in the said digital servo controller [5], in DEFCS numeral emergent backup flight control module [12], store emergent backup control law program, the signal output part of signal conditioning circuit [4] is connected with the input end of DEFCS numeral emergent backup flight control module [12], and the output terminal of DEFCS numeral emergent backup flight control module [12] is connected with the normally opened contact of active/standby change-over switch [11].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010260070 CN101916111A (en) | 2010-08-19 | 2010-08-19 | Electric drive flight control system structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010260070 CN101916111A (en) | 2010-08-19 | 2010-08-19 | Electric drive flight control system structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101916111A true CN101916111A (en) | 2010-12-15 |
Family
ID=43323637
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010260070 Pending CN101916111A (en) | 2010-08-19 | 2010-08-19 | Electric drive flight control system structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101916111A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105807761A (en) * | 2015-09-02 | 2016-07-27 | 南京乐朋电子科技有限公司 | Control system of bionic intelligent robotic fish |
| CN107406137A (en) * | 2014-11-26 | 2017-11-28 | 埃姆普里萨有限公司 | System and method for exchanging the flight control executor in aircraft flight control system and driving cabin |
| CN113386951A (en) * | 2021-08-17 | 2021-09-14 | 中国商用飞机有限责任公司 | Turning control system, method and computer-readable storage medium for aircraft |
| CN113534655A (en) * | 2021-09-07 | 2021-10-22 | 中国商用飞机有限责任公司 | Telex flight backup control system and starting method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5330131A (en) * | 1992-05-28 | 1994-07-19 | The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration | Engines-only flight control system |
| CN1358649A (en) * | 2002-01-29 | 2002-07-17 | 北京航空航天大学 | Self-check test for test-control and electronic system of axle-shared double-rotary wing pilotless helicopter |
| US20070164166A1 (en) * | 2006-01-17 | 2007-07-19 | Jukka Matti Hirvonen | Apparatus and method for backup control in a distributed flight control system |
| CN201000576Y (en) * | 2007-01-26 | 2008-01-02 | 青岛天骄无人机遥感技术有限公司 | Flight control system for unmanned plane |
| CN101799689A (en) * | 2010-04-08 | 2010-08-11 | 中国电子科技集团公司第三十八研究所 | Dual-redundancy steering engine controller |
-
2010
- 2010-08-19 CN CN 201010260070 patent/CN101916111A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5330131A (en) * | 1992-05-28 | 1994-07-19 | The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration | Engines-only flight control system |
| CN1358649A (en) * | 2002-01-29 | 2002-07-17 | 北京航空航天大学 | Self-check test for test-control and electronic system of axle-shared double-rotary wing pilotless helicopter |
| US20070164166A1 (en) * | 2006-01-17 | 2007-07-19 | Jukka Matti Hirvonen | Apparatus and method for backup control in a distributed flight control system |
| CN201000576Y (en) * | 2007-01-26 | 2008-01-02 | 青岛天骄无人机遥感技术有限公司 | Flight control system for unmanned plane |
| CN101799689A (en) * | 2010-04-08 | 2010-08-11 | 中国电子科技集团公司第三十八研究所 | Dual-redundancy steering engine controller |
Non-Patent Citations (2)
| Title |
|---|
| 《中国优秀硕士学位论文全文数据库》 20070101 杨林芳 无人机容错飞行控制系统研究 , 2 * |
| 《中国制造业信息化》 20060201 屈蔷 刘建业 梅劲松 自主无人机导航及数字飞行控制系统的研制 第35卷, 第3期 2 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107406137A (en) * | 2014-11-26 | 2017-11-28 | 埃姆普里萨有限公司 | System and method for exchanging the flight control executor in aircraft flight control system and driving cabin |
| CN107406137B (en) * | 2014-11-26 | 2020-04-28 | 埃姆普里萨有限公司 | System and method for interchanging flight control manipulators in an aircraft flight control system and cockpit |
| CN105807761A (en) * | 2015-09-02 | 2016-07-27 | 南京乐朋电子科技有限公司 | Control system of bionic intelligent robotic fish |
| CN105807761B (en) * | 2015-09-02 | 2019-07-12 | 南京乐朋电子科技有限公司 | A kind of control system of bionic intelligence machine fish |
| CN113386951A (en) * | 2021-08-17 | 2021-09-14 | 中国商用飞机有限责任公司 | Turning control system, method and computer-readable storage medium for aircraft |
| CN113386951B (en) * | 2021-08-17 | 2024-04-02 | 中国商用飞机有限责任公司 | Turning control system, method and computer readable storage medium for aircraft |
| CN113534655A (en) * | 2021-09-07 | 2021-10-22 | 中国商用飞机有限责任公司 | Telex flight backup control system and starting method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102662394B (en) | Fault simulation device for automobile electric power-assisted steering system | |
| CN103631178B (en) | A kind of double-unit backup redundancy control device | |
| CN101916111A (en) | Electric drive flight control system structure | |
| CN101799689A (en) | Dual-redundancy steering engine controller | |
| CN102419559A (en) | Train traction control system | |
| CN108375899B (en) | High-reliability wave glider control system | |
| CN203520080U (en) | Real-time controller of universal frequency converter | |
| CN103516346A (en) | A triplex redundancy simulation signal hardware voting circuit | |
| CN104595551A (en) | Three-redundancy servo valve driving circuit | |
| CN209230638U (en) | A kind of navigation control system based on multi-core processor | |
| CN204347604U (en) | A kind of industrial robot controller | |
| CN205121280U (en) | Redundant configuration systems of high accuracy star sensor of popping one's head in more | |
| CN109631893A (en) | A kind of navigation control system and its control method based on multi-core processor | |
| CN203060651U (en) | Intelligent fire truck control platform based on CAN bus | |
| CN205620739U (en) | Interface circuit is planned to general section mould of input/output | |
| CN103605328A (en) | STC single chip microcomputer-based embedded programmable logic controller (PLC) industrial control board | |
| CN202221317U (en) | Digital input output interface expanding device for testing vehicle electronic products | |
| CN214412612U (en) | Double-circuit hub servo motor driving and controlling system | |
| CN205753608U (en) | A kind of multiloop automatic change-over device of emergency | |
| CN203745856U (en) | Embedded PLC industrial control plate based on STC single-chip microcomputer | |
| CN202267835U (en) | Bi-module redundant heat standby measurement and control device | |
| CN103207584A (en) | Soft logic measuring and controlling system of marine auxiliary machine | |
| CN101140465A (en) | Ship auxiliary engine measurement and control system based on soft logic controller | |
| CN220419954U (en) | Multi-serial-port double-backup data storage processing system | |
| CN109164739B (en) | Electrohydraulic servo control system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Open date: 20101215 |