CN104192300B - A kind of flight control system and method - Google Patents
A kind of flight control system and method Download PDFInfo
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- CN104192300B CN104192300B CN201410162960.8A CN201410162960A CN104192300B CN 104192300 B CN104192300 B CN 104192300B CN 201410162960 A CN201410162960 A CN 201410162960A CN 104192300 B CN104192300 B CN 104192300B
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Abstract
The invention discloses a kind of flight control system and method, the system comprises: the actuator that at least one personnel's control member with Optical displacement sensor and electric displacement sensor, backup control module, the corresponding actuator control module of electric chain-circuit system, the corresponding actuator control module of optical link system and each actuator control module control respectively；The backup control module is used to generate control instruction from the coherent signal of the Optical displacement sensor or electric displacement sensor according to what is received；The corresponding actuator control module of the electricity chain-circuit system and the corresponding actuator control module of optical link system are used to drive corresponding actuator according to the control instruction received, to complete the control of aircraft rudder surface.The embodiment of the present invention in flight control system by using optical transport backup electrical transmission information to further improve the safety of flight control system to solve the problems, such as that the flight control system based on electrical transmission is unsatisfactory for dissimilar redundancy.
Description
Technical field
The present invention relates to technical field of flight control more particularly to a kind of flight control systems and method.
Background technique
Civil aircraft flight control system for security reasons, in addition to common normal mode, auxiliary mode, directly
Outside mode, it is generally also devised with backup mode, i.e. for aircraft in the case where important component malfunction or damage, aircraft can be in minimum
Land in the case where manipulation.With the development of flight control technology, the standby system of civil aircraft flight control is by past pure
The electricity backup of mechanical backup till now.Individual types are under the premise of meeting safety, it is contemplated that structure, weight etc. because
Element eliminates the design of standby system.
Standby system of the mechanical system as flight control, has reached one on the dissimilar redundancy of structure type
A good effect, but since the weight and volume of mechanical system is all bigger, with the development of electric standby system, by
Gradually it is substituted.There is biggish advantages in terms of weight and volume for electric standby system, but due to being the design of electric standby system
Do not meet the requirement of non-similar Design well, such as in the case where suffering from strong lightning stroke, lightning events, may cause including main flight
The entire paralysis of control system and electric standby system, therefore the safety of the scheme of electric standby system need to be improved.
Summary of the invention
In view of this, the embodiment of the invention provides a kind of flight control system and method, to further increase flight control
The safety of system processed.
On the one hand, the embodiment of the invention provides a kind of flight control system, the system comprises: at least one has light
Personnel's control member of displacement sensor and electric displacement sensor, backup control module, the corresponding actuator control of electric chain-circuit system
The actuator that the corresponding actuator control module of molding block, optical link system and each actuator control module control respectively；Its
In,
Each Optical displacement sensor is used to measure the displacement of counterpart personnel's control member, and by measurement result with optical signal
Form be sent to the backup control module；Each electric displacement sensor is used to measure the displacement of counterpart personnel's control member
Amount, and send measurement result to as electronic signals the backup control module；
The backup control module is used to generate control instruction according to the electric signal from electric displacement sensor received,
It sends the corresponding actuator control module of electric chain-circuit system as electronic signals by the control instruction；And according to reception
The optical signal from Optical displacement sensor arrived generates control instruction, and light chain is sent in the form of optical signal by the control instruction
The corresponding actuator control module of road system；
The corresponding actuator control module of the electricity chain-circuit system is used for according to receiving from the Standby control mould
The electric signal of block drives corresponding actuator, to complete the control of aircraft rudder surface；The corresponding actuator control of the optical link system
Molding block is used for according to the corresponding actuator of optical signal driving received from the backup control module, to complete aircraft rudder
The control in face.
Further, personnel's control member includes aircraft side lever and pedal.
Further, the backup control module includes field programmable gate array FPGA interface, and the FPGA connects
Mouth generates control instruction for receiving the optical signal from Optical displacement sensor, according to the optical signal received, which is referred to
Order is sent to the corresponding actuator control module of optical link system in the form of optical signal, and receives and come from electric displacement sensor
Electric signal, generate control instruction based on the received electrical signal, send current source as electronic signals for the control instruction
The corresponding actuator control module of road system.
Further, the corresponding actuator control module of the optical link system includes FPGA interface, the FPGA interface
For receiving the optical signal from the backup control module, the optical signal received is converted into electric signal.
Further, the transmission link of electric signal and the transmission link of optical signal are mutually indepedent in the system.
On the other hand, the embodiment of the invention also provides a kind of flight control method based on above-mentioned flight control system,
Include:
Optical displacement sensor measures the displacement of counterpart personnel's control member, and measurement result is sent out in the form of optical signal
It is sent to the backup control module；Electric displacement sensor measure counterpart personnel's control member displacement, and by measurement result with
The form of electric signal is sent to backup control module；
The backup control module generates control instruction according to the electric signal from electric displacement sensor received, by this
Control instruction is sent to the corresponding actuator control module of electric chain-circuit system as electronic signals；And according to receiving
Optical signal from Optical displacement sensor generates control instruction, and optical link system is sent in the form of optical signal by the control instruction
It unites corresponding actuator control module；
The electricity chain-circuit system corresponding actuator control module is according to receiving from the backup control module
Electric signal drives corresponding actuator, to complete the control of aircraft rudder surface；The corresponding actuator of the optical link system controls mould
Root tuber drives corresponding actuator according to the optical signal from the backup control module is received, to complete the control of aircraft rudder surface
System.
Further, the backup control module uses field programmable gate array FPGA interface, and the FPGA connects
Mouthful receive the optical signal from Optical displacement sensor, control instruction generated according to the optical signal that receives, by the control instruction with
The form of optical signal is sent to the corresponding actuator control module of optical link system, and receives the electricity from electric displacement sensor
Signal generates control instruction based on the received electrical signal, sends current source road system as electronic signals for the control instruction
It unites corresponding actuator control module.
Further, the corresponding actuator control module of the optical link system uses FPGA interface, the FPGA interface
The optical signal from the backup control module is received, the optical signal received is converted into electric signal.
Further, the corresponding actuator control module of the optical link system is controlled according to what is received from the backup
The optical signal of molding block drives corresponding actuator, to complete the control of aircraft rudder surface, comprising:
The corresponding actuator control module of the optical link system by the FPGA interface will receive from described
The optical signal of backup control module is converted to electric signal；
The corresponding actuator control module of the optical link system drives corresponding actuator according to the electric signal, with complete
At the control of aircraft rudder surface.
Further, the transmission link of electric signal and the transmission link of optical signal are mutually indepedent in the method.
Flight control system and method provided in an embodiment of the present invention, by using optical transport standby in flight control system
Part electrical transmission information, to solve the problems, such as that the flight control system based on electrical transmission is unsatisfactory for dissimilar redundancy, further
Improve the safety of flight control system.
Detailed description of the invention
Fig. 1 is the schematic diagram of flight control system provided in an embodiment of the present invention；
Fig. 2 is the schematic diagram of FPGA interface in flight control system provided in an embodiment of the present invention；
Fig. 3 is a kind of preferred flight control system architecture diagram provided in an embodiment of the present invention；
Fig. 4 is a kind of preferred standby system schematic diagram in flight control system provided in an embodiment of the present invention；
Fig. 5 is the flow chart of flight control method provided in an embodiment of the present invention；
Fig. 6 is the work of the corresponding actuator control module of standby system in flight control method provided in an embodiment of the present invention
Make flow chart.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining the present invention rather than limiting the invention.It also should be noted that in order to just
In description, only some but not all contents related to the present invention are shown in the drawings.
Fig. 1 shows the schematic diagram of flight control system provided in an embodiment of the present invention, as shown in Figure 1, the system packet
Include: at least one has personnel's control member 11, the backup control module 12, current source of Optical displacement sensor and electric displacement sensor
The corresponding actuator control module 13 of road system, the corresponding actuator control module 14 of optical link system and the control of each actuator
The actuator 15 that module controls respectively.Wherein, each Optical displacement sensor is for measuring counterpart personnel's control member 11
Displacement, and send measurement result in the form of optical signal the backup control module 12；Each electric displacement sensor is used
In the displacement of measurement counterpart personnel's control member 11, and send measurement result to as electronic signals the Standby control
Module 12；The backup control module 12, which is used to generate control according to the electric signal from electric displacement sensor received, to be referred to
It enables, sends the corresponding actuator control module 13 of electric chain-circuit system as electronic signals for the control instruction；And according to
The optical signal from Optical displacement sensor received generates control instruction, sends the control instruction in the form of optical signal
The corresponding actuator control module 14 of optical link system；The corresponding actuator control module 13 of the electricity chain-circuit system is used for basis
The electric signal from the backup control module 12 received drives corresponding actuator 15, to complete the control of aircraft rudder surface
System；The corresponding actuator control module 14 of the optical link system is used for according to receiving from the backup control module 12
Optical signal drives corresponding actuator 15, and to complete the control of aircraft rudder surface, the control of the aircraft rudder surface includes on the outside of aircraft
Aileron, upside elevator, outer elevator and horizontal stabilizer control or aircraft inner aileron, downside elevator, inside
The control of elevator and horizontal stabilizer.In the present embodiment, the electricity chain-circuit system and optical link system can be respectively completed one
The control of group aircraft rudder surface.
Flight control system provided in an embodiment of the present invention in flight control system by using optical transport backup fax
Defeated information further improves to solve the problems, such as that the flight control system based on electrical transmission is unsatisfactory for dissimilar redundancy
The safety of flight control system.
In above-described embodiment, personnel's control member 11 generally includes aircraft side lever and pedal, and the aircraft side lever can
To include main driving side lever and copilot side lever.It is mounted on optical sensor and electric transducer on the aircraft side lever and pedal,
Aircrew can personnel's control member 11 described in flexible operating.The optical sensor can according to the operation of the aircrew,
The displacement of personnel's control member 11 is obtained, and sends the Standby control in the form of optical signal for the displacement
Module 12, the electric transducer can obtain the displacement of personnel's control member 11 according to the operation of the aircrew,
And it sends the backup control module 12 as electronic signals by the displacement.
In above-described embodiment, the backup control module 12 may include FPGA (Field Programmable Gate
Array, field programmable gate array) interface, the FPGA interface for receiving the electric signal from electric displacement sensor,
And control instruction is generated based on the received electrical signal, it sends electric chain-circuit system pair as electronic signals by the control instruction
The actuator control module 13 answered and the FPGA interface are for receiving the optical signal from Optical displacement sensor, according to connecing
The optical signal received generates control instruction, and the corresponding actuation of optical link system is sent in the form of optical signal by the control instruction
Device control module 14.The FPGA is a kind of highly integrated chip, can directly carry out the transmission of electric signal and optical signal, institute
The data received can also be handled by stating FPGA, such as parsed to the data received, is subsequent according to data progress
The state judgement of component carries out operation etc. to data.
The interface of the FPGA is as shown in Fig. 2, include FPGA optical interface and FPGA electrical interface, the FPGA optical interface includes
Receiving interface of optical 1, light transmission interface 1, receiving interface of optical 2 and light transmission interface 2, the FPGA electrical interface include electric receiving interface
1, electric transmission interface 1, electric receiving interface 2 and electric transmission interface 2.Wherein, the receiving interface of optical 1, light transmission interface 1, electricity connect
Receiving interface 1 and electric transmission interface 1 is host computer interface, can be communicated with host computer by host computer interface, the light is sent
Interface 2, receiving interface of optical 2, electric transmission interface 2 and electric receiving interface 2 are slave computer interface, can be with bottom by slave computer interface
Machine is communicated.For example, for backup control module, host computer interface can be used for receiving the optical signal for carrying out Optical displacement sensor and
Electric signal, slave computer interface can be used for sending optical signal to the corresponding actuator control module of optical link system, and to current source
System corresponding actuator control module in road sends electric signal.
In above-described embodiment, the corresponding actuator control module 14 of the optical link system may include FPGA interface, described
The optical signal received is converted to telecommunications for receiving the optical signal from the backup control module 12 by FPGA interface
Number.
In addition, in the embodiment of the present invention, the backup control module 12, the corresponding actuator control module of electric chain-circuit system
13, the corresponding actuator control module 14 of optical link system may each comprise FPGA interface, and the FPGA interface includes that FPGA electricity connects
Mouthful and FPGA optical interface be received and transmitted using the FPGA electrical interface, when the signal received is electric signal when connecing
When the signal received is optical signal, it is received and transmitted using the FPGA optical interface.
Optical signal transmission is carried out using FPGA in the present embodiment, reduces the type of device in backup control module, such as nothing
It need to be mentioned using the conversion that photoelectric conversion module and electrooptic conversion module carry out signal to reduce the complexity of hardware design
The high reliability of system.
In above-described embodiment, the transmission link of electric signal and the transmission link of optical signal are mutually indepedent in the system.Appoint
One transmission link, which breaks down, will not influence the normal work of another transmission link.Fig. 3 shows one kind and is preferably based on light
The flight control system architecture diagram of electrical transmission, as shown in figure 3, electric chain-circuit system uses electric signal transmission, such as Fig. 3 in the system
Shown in middle dotted arrow, optical signal transmission is used in optical link system, as shown in solid arrow in Fig. 3.As shown in figure 3, being located at
Optical displacement sensor and electric displacement sensor in personnel's control member measure the displacement of personnel's control member, and by institute
State displacement and be sent to the backup control module in the form of optical signal and electric signal respectively, the backup control module according to
The electric signal received generates control instruction, is sent to the corresponding actuator control module of electric chain-circuit system, drives corresponding actuation
The control of device completion aircraft rudder surface；The backup control module generates control instruction according to the optical signal received, is sent to light
The corresponding actuator control module of chain-circuit system drives corresponding actuator to complete the control of aircraft rudder surface.Wherein, the current source road
The corresponding actuator control module of system include outer aileron actuator control module, downside elevator actuator control module,
Outer elevator actuator control module and horizontal stabilizer actuator control module, the electricity chain-circuit system can complete outside
The control of aileron, downside elevator, outer elevator and horizontal stabilizer；The corresponding actuator of the optical link system controls mould
Block includes inner aileron actuator control module, upside elevator actuator control module, inside elevator actuator control mould
Block and horizontal stabilizer actuator control module, the optical link system can complete inner aileron, upside elevator, inside liter
The control of rudder and horizontal stabilizer is dropped.Under normal conditions, electric chain-circuit system and optical link system can carry out the biography of signal simultaneously
It is defeated, when in electric chain-circuit system unit failure or electric signal be obstructed when, can be used optical link system control aircraft complete flight
Work.
Fig. 4 shows a kind of schematic diagram of preferred standby system in Fig. 3, as shown in figure 4, main driving side lever, copilot
Side lever and pedal are personnel's control member, and Optical displacement sensor is respectively arranged on personnel's operating member, and the light displacement passes
The information of sensor output is sent to backup control module, the backup control module by FPGA interface to the information received into
The corresponding each actuator control module of optical link system is re-send to after row processing, each actuator control module can pass through inside
FPGA interface drives corresponding actuator to complete the control of aircraft rudder surface, wherein the corresponding each actuator control of the optical link system
Molding block includes aileron control module on the left of inside, aileron control module on the right side of inside, elevator control module on the left of inside, interior
Elevator control module, upside elevator control module and horizontal stabilizer control module, the optical link system pair on the right side of side
Aileron, inside right side aileron, inside left side elevator, inside right side rise on the left of the achievable inside of each actuator control module answered
The control of rudder, upside elevator and horizontal stabilizer is dropped.
Backup control module and the corresponding actuator control module of optical link system are all made of integrated in the embodiment of the present invention
Formula FPGA interface realizes the full optical link of flight control optical link system, solves the problems, such as the dissimilar redundancy in system, into
And improve the safety of flight control system.
Fig. 5 shows the flow chart of flight control method provided in an embodiment of the present invention, and the method is by above-described embodiment
The flight control system of offer executes.As shown in figure 4, details are as follows for the process:
The displacement of step 501, Optical displacement sensor measurement counterpart personnel's control member, and by measurement result with optical signal
Form be sent to the backup control module；Electric displacement sensor measures the displacement of counterpart personnel's control member, and will survey
Amount result is sent to backup control module as electronic signals.
Step 502, the backup control module generate control according to the electric signal from electric displacement sensor received
Instruction, sends the corresponding actuator control module of electric chain-circuit system for the control instruction as electronic signals；And according to
The optical signal from Optical displacement sensor received generates control instruction, sends the control instruction in the form of optical signal
The corresponding actuator control module of optical link system.
Step 503, the corresponding actuator control module of the electricity chain-circuit system are controlled according to what is received from the backup
The electric signal of molding block drives corresponding actuator, to complete the control of aircraft rudder surface；The corresponding actuation of the optical link system
Device control module drives corresponding actuator according to the optical signal received from the backup control module, to complete aircraft rudder
The control in face.
In the present embodiment, the backup control module uses field programmable gate array FPGA interface, the FPGA
Interface can receive the optical signal from Optical displacement sensor, control instruction be generated according to the optical signal received, by the control
Instruction is sent to the corresponding actuator control module of optical link system in the form of optical signal, and receives and sense from dielectric displacement
The electric signal of device, generates control instruction based on the received electrical signal, sends electricity as electronic signals for the control instruction
The corresponding actuator control module of chain-circuit system.
In the present embodiment, the corresponding actuator control module of the optical link system uses FPGA interface, and the FPGA connects
Mouth receives the optical signal from the backup control module, and the optical signal received is converted to electric signal.
In addition, in the embodiment of the present invention, the backup control module, the corresponding actuator control module of electric chain-circuit system,
The corresponding actuator control module of optical link system may each comprise FPGA interface, the FPGA interface include FPGA electrical interface and
FPGA optical interface is received and transmitted, when receiving when the signal received is electric signal using the FPGA electrical interface
Signal be optical signal when, be received and transmitted using the FPGA optical interface.
In the present embodiment, the corresponding actuator control module of the optical link system is according to receiving from the backup
The optical signal of control module drives corresponding actuator, to complete the control of aircraft rudder surface, including step shown in fig. 6:
Step 601, the optical link system corresponding actuator control module will be received by the FPGA interface
Optical signal from the backup control module is converted to electric signal.
Step 602, the corresponding actuator control module of the optical link system drive corresponding work according to the electric signal
Dynamic device, to complete the control of aircraft rudder surface.
In the present embodiment, the transmission link of electric signal and the transmission link of optical signal are mutually indepedent.
Flight control method flight control system provided by the above embodimen provided in an embodiment of the present invention executes, can
Reach technical effect similar with the flight control system, details are not described herein.
Obviously, it will be understood by those skilled in the art that each module of the above invention or each step can be with general
Computing device realizes that they can be concentrated on single computing device, or be distributed in net constituted by multiple computing devices
On network, optionally, they can be realized with the program code that computer installation can be performed, and be deposited so as to be stored in
It is performed by computing device in storage device, perhaps they are fabricated to each integrated circuit modules or will be in them
Multiple modules or step are fabricated to single integrated circuit module to realize.In this way, the present invention is not limited to any specific hardware
With the combination of software.
The above description is only a preferred embodiment of the present invention, is not intended to restrict the invention, for those skilled in the art
For, the invention can have various changes and changes.All any modifications made within the spirit and principles of the present invention are equal
Replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (9)
1. a kind of flight control system, which is characterized in that the system comprises: at least one has Optical displacement sensor and current potential
Personnel's control member of displacement sensor, backup control module, the corresponding actuator control module of electric chain-circuit system, optical link system
The actuator that corresponding actuator control module and each actuator control module control respectively；Wherein,
Each Optical displacement sensor is used to measure the displacement of counterpart personnel's control member, and by measurement result with the shape of optical signal
Formula is sent to the backup control module；Each electric displacement sensor is used to measure the displacement of counterpart personnel's control member, and
Send measurement result to as electronic signals the backup control module；
The backup control module is used to generate control instruction according to the electric signal from electric displacement sensor received, by this
Control instruction is sent to the corresponding actuator control module of electric chain-circuit system as electronic signals；And according to receiving
Optical signal from Optical displacement sensor generates control instruction, and optical link system is sent in the form of optical signal by the control instruction
It unites corresponding actuator control module；
The electricity chain-circuit system corresponding actuator control module is used for according to receiving from the backup control module
Electric signal drives corresponding actuator, to complete the control of aircraft rudder surface；Meanwhile the corresponding actuator control of the optical link system
Molding block is used for according to the corresponding actuator of optical signal driving received from the backup control module, to complete aircraft rudder
The control in face；And
Wherein, personnel's control member includes aircraft side lever and pedal.
2. flight control system according to claim 1, which is characterized in that the backup control module includes that scene can compile
Journey logic gate array FPGA interface, the FPGA interface is for receiving the optical signal from Optical displacement sensor, according to receiving
Optical signal generate control instruction, the corresponding actuator control of optical link system is sent in the form of optical signal by the control instruction
Molding block, and the electric signal from electric displacement sensor is received, control instruction is generated based on the received electrical signal, by the control
System instruction is sent to the corresponding actuator control module of electric chain-circuit system as electronic signals.
3. flight control system according to claim 1, which is characterized in that the corresponding actuator control of the optical link system
Molding block includes FPGA interface, and the FPGA interface will be received for receiving the optical signal from the backup control module
To optical signal be converted to electric signal.
4. flight control system according to claim 1, which is characterized in that in the system transmission link of electric signal and
The transmission link of optical signal is mutually indepedent.
5. a kind of flight control method based on the flight control system any in claim 1-4, which is characterized in that packet
It includes:
Optical displacement sensor measures the displacement of counterpart personnel's control member, and sends measurement result in the form of optical signal
The backup control module；Electric displacement sensor measures the displacement of counterpart personnel's control member, and by measurement result with telecommunications
Number form be sent to backup control module；
The backup control module generates control instruction according to the electric signal from electric displacement sensor received, by the control
Instruction is sent to the corresponding actuator control module of electric chain-circuit system as electronic signals；And it is come from according to what is received
The optical signal of Optical displacement sensor generates control instruction, and optical link system pair is sent in the form of optical signal by the control instruction
The actuator control module answered；
The corresponding actuator control module of the electricity chain-circuit system is according to the telecommunications from the backup control module received
Number corresponding actuator of driving, to complete the control of aircraft rudder surface；Meanwhile the corresponding actuator of the optical link system controls mould
Root tuber drives corresponding actuator according to the optical signal from the backup control module is received, to complete the control of aircraft rudder surface
System.
6. flight control method according to claim 5, which is characterized in that the backup control module can be compiled using scene
Journey logic gate array FPGA interface, the FPGA interface receives the optical signal from Optical displacement sensor, according to the light received
Signal generates control instruction, sends the corresponding actuator of optical link system in the form of optical signal for the control instruction and controls mould
Block, and, the electric signal from electric displacement sensor is received, control instruction is generated based on the received electrical signal, by the control
Instruction is sent to the corresponding actuator control module of electric chain-circuit system as electronic signals.
7. flight control method according to claim 5, which is characterized in that the corresponding actuator control of the optical link system
Molding block uses FPGA interface, and the FPGA interface receives the optical signal from the backup control module, by what is received
Optical signal is converted to electric signal.
8. flight control method according to claim 7, which is characterized in that the corresponding actuator control of the optical link system
Molding root tuber drives corresponding actuator according to the optical signal from the backup control module received, to complete aircraft rudder surface
Control, comprising:
The corresponding actuator control module of the optical link system by the FPGA interface will receive from the backup
The optical signal of control module is converted to electric signal；
The corresponding actuator control module of the optical link system drives corresponding actuator according to the electric signal, to complete to fly
The control of machine rudder face.
9. flight control method according to claim 5, which is characterized in that in the method the transmission link of electric signal and
The transmission link of optical signal is mutually indepedent.
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| CN201410162960.8A CN104192300B (en) | 2014-04-22 | 2014-04-22 | A kind of flight control system and method |
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| CN201410162960.8A CN104192300B (en) | 2014-04-22 | 2014-04-22 | A kind of flight control system and method |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105550077B (en) * | 2015-12-10 | 2019-02-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Standby control system |
| CN105857581B (en) * | 2016-05-19 | 2018-10-02 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of aircraft cockpit steerable system and method for operating |
| CN110884678B (en) * | 2019-12-04 | 2023-05-26 | 中国直升机设计研究所 | Displacement sensor arrangement method for fly-by-wire control system of helicopter |
| 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 |
| CN113504720A (en) * | 2021-09-07 | 2021-10-15 | 中国商用飞机有限责任公司 | Backup control system based on distributed fly-by-wire architecture and working method |
| CN113534656B (en) * | 2021-09-07 | 2022-01-21 | 中国商用飞机有限责任公司 | Telex flight backup control system and telex flight backup control method |
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| DE3713717A1 (en) * | 1987-04-24 | 1988-11-10 | Messerschmitt Boelkow Blohm | AIRCRAFT CONTROL DEVICE FOR AIRCRAFT |
| CN1202442A (en) * | 1997-03-14 | 1998-12-23 | 国家航空工业公司 | Control process and device for aircraft roll or pitch control surface |
| CN201371945Y (en) * | 2008-12-29 | 2009-12-30 | 中国航天科技集团公司烽火机械厂 | Electric steering engine controller based on FPGA |
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|---|---|---|---|---|
| DE3713717A1 (en) * | 1987-04-24 | 1988-11-10 | Messerschmitt Boelkow Blohm | AIRCRAFT CONTROL DEVICE FOR AIRCRAFT |
| CN1202442A (en) * | 1997-03-14 | 1998-12-23 | 国家航空工业公司 | Control process and device for aircraft roll or pitch control surface |
| CN201371945Y (en) * | 2008-12-29 | 2009-12-30 | 中国航天科技集团公司烽火机械厂 | Electric steering engine controller based on FPGA |
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| CN104192300A (en) | 2014-12-10 |
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