CN106628123A - Distributed airplane flap control system - Google Patents
Distributed airplane flap control system Download PDFInfo
- Publication number
- CN106628123A CN106628123A CN201611237461.6A CN201611237461A CN106628123A CN 106628123 A CN106628123 A CN 106628123A CN 201611237461 A CN201611237461 A CN 201611237461A CN 106628123 A CN106628123 A CN 106628123A
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- Prior art keywords
- flap
- control
- computer
- flap control
- sensor
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
- B64C13/504—Transmitting means with power amplification using electrical energy using electro-hydrostatic actuators [EHA's]
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Safety Devices In Control Systems (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
The invention discloses a distributed airplane flap control system. The distributed airplane flap control system comprises a flap control handle, a flap override control panel, a flap control computer, a flap position sensor, a flap inclination sensor and flap driving actuators. The flap control handle and the flap override control panel are command input devices for the normal state and the emergency state respectively. The emergency state is the system state when flap closed loop control fails. The flap control computer is the key device of the system, collects command input signals and position feedback signals and outputs digital control signals to the flap driving actuators. Each flap driving actuator comprises a servo controller which converts the digital signals obtained from the computer into servo driving signals, electromagnetic and serve valves are driven to move, and accordingly a flap is driven to move. The distributed airplane flap control system is small in device number, high in basic reliability and task reliability, convenient to maintain and suitable for novel universal carrier planes.
Description
Technical field
The invention belongs to the Design of Flight Control field of field of airplane design, and in particular to a kind of distributed wing flap
Control system.
Background technology
In current aircraft design field, centralized wing flap control system has been widely applied, particularly in aircarrier aircraft
In, but with the thinking phase analogy of the distributed driving of Flying by wire system, wing flap control system can also take distributed driving
Thinking, simultaneously because the development of computer technology so that wing flap control system is more favorable for implementing using distributed driving.
In the aircarrier aircrafts such as Boeing, Air Passenger, centralized type of drive is all adopted at present, wherein, Airbus Aircraft is adopted
The Power Drive Unit of two hydraulic motors, Boeing adopts the standby Power Drive Unit of the main electricity of liquid, then will by mechanical linear system
Moment of torsion is delivered to rudder face, realizes the motion control of rudder face, and the great advantage of centralized driving is to ensure that the synchronization of motion of rudder
Property, but there is also the shortcomings of equipment composition is complicated, and mechanical linear system has Single Point of Faliure, working service is inconvenient.Carefully inquiry is provided
Find after material, distributed driving is also applied in minority aircraft, such as C17, MD10 etc., but is limited to electronics skill at that time
Art level, distributed wing flap control system performance in the application is barely satisfactory.At present the level of electronic computer has developed
To a new height, good synchronous effect can also be obtained using distributed type of drive, while also bringing structure
Simply, easy to maintenance, high reliability is particularly well-suited to need the aircraft of wing-folding, for example carrier-on-board aircraft, carrier-borne
Early warning plane.
The content of the invention
The purpose of the present invention is：A kind of distributed wing flap Control System Design framework is provided, control wing flap rudder face fortune is reached
Dynamic purpose, while its simple structure, easy to maintenance, is particularly well-suited to need the aircraft of wing-folding and Small General Aircraft.
The technical scheme is that：A kind of distributed aircraft flap control system, including flap control handle, wing flap surpasses
Control control panel, flap control computers, flap position transducer, flap cant sensor, wing flap drive ram, wherein：
Flap control handle and wing flap override control panel are connected with control core flap control computers, normal mode
Under, by the displacement transducer of handle by pilot command's signal input computer, when normal mode fails, by override control
Making sheet is directly sent to discrete command signal in actuator controller, reaches the purpose of the emergent start of control actuator, wing flap
Position sensor and flap cant sensor are sensitive detection means, by measurement position information, reach position closed loop and to flying
Office staff provides the effect of positional information, while monitoring the moving situation of rudder face, when motion occur and being asynchronous, reporting fault inclines
Tiltedly there is inclined situation, the reporting fault when inclination is detected in sensor detection rudder face.Flap drive is system start
Mechanism, simultaneous with servo control module, after the numerical control instruction for receiving computer, the servo for completing actuator is driven
It is dynamic, data signal is converted into into current signal；
Flap control computers are system control device, gather the instruction input information of pilot, and in position feedback letter
Breath is comprehensive, calculates numerical control instruction, while the working condition of monitoring system, wing flap control system is by two wing flap control meters
Calculation machine is constituted, and every computer-internal is controlling brancher and monitoring branch road binary channels, self-monitoring purpose is reached, when a calculating
When machine breaks down, another computer export control instruction in Hot Spare reaches primary fault work, twice failure peace
Full system reliability ability.Displacement transducer is instructed to be RVDT forms in flap control handle；Flap position transducer is for just
Cosine forms of sensor；Flap cant sensor is proximity transducer form；Flap drive is hydraulic driving mode, is calculated
Machine reaches the purpose of control actuator motion by controlling magnetic valve and servo valve；Flap control computers are for control and monitor double
Branch road, using non-similar Design theory, improves security, the reliability of system from form is monitored.
Beneficial effect produced by the present invention：A kind of distributed wing flap control system framework form of the present invention, reaches flight
The function of member's control flap kinematics, realizes lift-rising of the aircraft in the take-off and landing stage.Compared with centralized wing flap control system,
There is simple structure, easy to maintenance, suitable wing-folding.
Description of the drawings
Fig. 1 is a kind of distributed wing flap control system architecture principle figure of the present invention；
Wherein, wing flap rudder face is that left and right is each two pieces, comprising two actuator and a position sensor on every piece of rudder face, two
It is an inclination sensor between block rudder face, flap control handle and wing flap override control panel are one, flap control computers
For two, the purpose of mutual backup is reached.
Specific embodiment
The present invention is described in further detail with reference to Figure of description, refers to Fig. 1.
Embodiment 1：A kind of distributed wing flap Control System Design framework, comprising manipulation device, control device, driving means
With sensitive detection means, the purpose that control wing flap rudder face is intended to motion according to pilot is reached.Flap control handle and wing flap control
Computer connection processed, two remainings in every computer acquisition handle instruction remaining signal of displacement transducer four, wing flap override control
Making sheet is connected with wing flap actuator servo control module, and flap position transducer is four remaining sine and cosine sensors, calculates per platform
Machine gathers two remaining signals.
Under system worked well mode, the controlling brancher and monitoring branch road of flap control computers gather refer to all the way respectively
Signal and all the way position feed back signal are made, validity monitoring is carried out after Cross transfer, the information after voting is sent into into control law solution
Unit is calculated, digital controlled signal is calculated, under normal circumstances, wing flap override control panel does not work, in addition a wing flap control meter
The work of calculation machine but not output order, wing flap actuator receives numerical control instruction signal and simultaneously drives motion of rudder.
In the system failure, flap kinematics are controlled using wing flap override control panel, now system is operated in emergent mode, point
Cloth actuator directly receives the discrete control signal of override plate, motion of rudder is driven, when actuator failure, it is impossible to which entering should
Anxious operation mode.
Displacement transducer is instructed to be RVDT forms in the flap control handle；
The flap position transducer is sine and cosine forms of sensor；
The flap cant sensor is proximity transducer form；
The flap drive is hydraulic driving mode, and computer reaches control and make by controlling magnetic valve and servo valve
The purpose of dynamic device motion；
The flap control computers are for control and monitor double branch roads from form is monitored, and using non-similar Design theory, carry
The security of high system, reliability.
Claims (1)
1. a kind of distributed aircraft flap control system, it is characterised in that including flap control handle, wing flap override control panel, 2
Platform flap control computers, flap position transducer, flap cant sensor, wing flap drive ram, wherein：
Flap control handle and wing flap override control panel are connected with flap control computers, under normal mode, by handle
Displacement transducer by pilot command's signal input computer, when normal mode fails, directly will be from by override control panel
Scattered command signal is sent in actuator controller, reaches the purpose of the emergent start of control actuator, flap position transducer and
Flap cant sensor is sensitive detection means, by measurement position information, reaches position closed loop and provides position to pilot
The effect of information, while the moving situation of rudder face is monitored, when there is motion and being asynchronous, reporting fault, inclination sensor detection
There is inclined situation, the reporting fault when inclination is detected in rudder face, and flap drive is system actuation mechanism, simultaneous with
Servo control module, after the numerical control instruction for receiving computer, completes the servo-drive of actuator, and data signal is turned
Turn to current signal；
Flap control computers are system control device, gather the instruction input information of pilot, and comprehensive in position feedback information
Close, calculate numerical control instruction, while the working condition of monitoring system, wing flap control system is by two flap control computers
Composition, every computer-internal is controlling brancher and monitoring branch road binary channels, self-monitoring purpose is reached, when a computer goes out
During existing failure, another computer export control instruction in Hot Spare reaches primary fault work, fail-safe twice
System reliability ability；Displacement transducer is instructed to be RVDT forms in flap control handle；Flap position transducer is sine and cosine
Forms of sensor；Flap cant sensor is proximity transducer form；Flap drive is hydraulic driving mode, and computer leads to
Cross control magnetic valve and servo valve reaches the purpose of control actuator motion；Flap control computers are for control and monitor double branch roads
From monitoring form, using non-similar Design theory, security, the reliability of system are improved.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611237461.6A CN106628123A (en) | 2016-12-28 | 2016-12-28 | Distributed airplane flap control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611237461.6A CN106628123A (en) | 2016-12-28 | 2016-12-28 | Distributed airplane flap control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106628123A true CN106628123A (en) | 2017-05-10 |
Family
ID=58832039
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611237461.6A Pending CN106628123A (en) | 2016-12-28 | 2016-12-28 | Distributed airplane flap control system |
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| CN (1) | CN106628123A (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107719639A (en) * | 2017-09-12 | 2018-02-23 | 陕西飞机工业（集团）有限公司 | A kind of double remaining wing flap automatic control systems |
| CN108016604A (en) * | 2017-11-23 | 2018-05-11 | 中国航空工业集团公司西安航空计算技术研究所 | The control method of override mode in a kind of wing flap control system |
| CN108170119A (en) * | 2017-12-08 | 2018-06-15 | 中国航空工业集团公司成都飞机设计研究所 | A kind of front and rear cabin flight control system instruction integrated approach in combat trainer |
| WO2019024401A1 (en) * | 2017-07-31 | 2019-02-07 | 中国商用飞机有限责任公司 | Flap/slat control lever |
| CN109443314A (en) * | 2018-10-24 | 2019-03-08 | 庆安集团有限公司 | A kind of high-lift system slant detection method |
| CN110667826A (en) * | 2019-09-03 | 2020-01-10 | 中国航空工业集团公司西安飞行自动控制研究所 | High-lift distributed telex control system |
| CN110716584A (en) * | 2019-10-29 | 2020-01-21 | 中国航空工业集团公司西安飞行自动控制研究所 | Automatic detection method in flight control system for actuator SOV fault |
| CN111003155A (en) * | 2019-12-27 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Method for flap control system with high reliability and low cost |
| CN111439390A (en) * | 2020-04-21 | 2020-07-24 | 中国商用飞机有限责任公司 | Slat system |
| CN112373704A (en) * | 2020-11-17 | 2021-02-19 | 中国商用飞机有限责任公司 | System for realizing emergency control of airplane by controlling engine thrust and airplane |
| CN114560074A (en) * | 2021-12-30 | 2022-05-31 | 中国航空工业集团公司西安飞机设计研究所 | Flap control system and flap control instruction calculation method |
| WO2023035497A1 (en) * | 2021-09-07 | 2023-03-16 | 中国商用飞机有限责任公司 | Fly-by-wire flight backup control system and method |
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| US5446666A (en) * | 1994-05-17 | 1995-08-29 | The Boeing Company | Ground state-fly state transition control for unique-trim aircraft flight control system |
| WO2011095360A1 (en) * | 2010-02-05 | 2011-08-11 | Airbus Operations Gmbh | Aircraft with a flow control device |
| CN104527970A (en) * | 2014-12-04 | 2015-04-22 | 中国航空工业集团公司第六三一研究所 | Distributed large airplane flap control computer system |
| CN204623824U (en) * | 2015-05-05 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | A kind of flight control system |
-
2016
- 2016-12-28 CN CN201611237461.6A patent/CN106628123A/en active Pending
Patent Citations (4)
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| US5446666A (en) * | 1994-05-17 | 1995-08-29 | The Boeing Company | Ground state-fly state transition control for unique-trim aircraft flight control system |
| WO2011095360A1 (en) * | 2010-02-05 | 2011-08-11 | Airbus Operations Gmbh | Aircraft with a flow control device |
| CN104527970A (en) * | 2014-12-04 | 2015-04-22 | 中国航空工业集团公司第六三一研究所 | Distributed large airplane flap control computer system |
| CN204623824U (en) * | 2015-05-05 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | A kind of flight control system |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019024401A1 (en) * | 2017-07-31 | 2019-02-07 | 中国商用飞机有限责任公司 | Flap/slat control lever |
| US11396361B2 (en) | 2017-07-31 | 2022-07-26 | Commercial Aircraft Corporation of China, Ltd. | Flap slat control lever |
| CN107719639A (en) * | 2017-09-12 | 2018-02-23 | 陕西飞机工业（集团）有限公司 | A kind of double remaining wing flap automatic control systems |
| CN108016604A (en) * | 2017-11-23 | 2018-05-11 | 中国航空工业集团公司西安航空计算技术研究所 | The control method of override mode in a kind of wing flap control system |
| CN108016604B (en) * | 2017-11-23 | 2021-05-07 | 中国航空工业集团公司西安航空计算技术研究所 | Control method for overriding mode in flap control system |
| CN108170119B (en) * | 2017-12-08 | 2020-06-30 | 中国航空工业集团公司成都飞机设计研究所 | Instruction integration method for flight control system of front cabin and rear cabin in combat trainer |
| CN108170119A (en) * | 2017-12-08 | 2018-06-15 | 中国航空工业集团公司成都飞机设计研究所 | A kind of front and rear cabin flight control system instruction integrated approach in combat trainer |
| CN109443314A (en) * | 2018-10-24 | 2019-03-08 | 庆安集团有限公司 | A kind of high-lift system slant detection method |
| CN110667826A (en) * | 2019-09-03 | 2020-01-10 | 中国航空工业集团公司西安飞行自动控制研究所 | High-lift distributed telex control system |
| CN110716584A (en) * | 2019-10-29 | 2020-01-21 | 中国航空工业集团公司西安飞行自动控制研究所 | Automatic detection method in flight control system for actuator SOV fault |
| CN111003155A (en) * | 2019-12-27 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Method for flap control system with high reliability and low cost |
| CN111439390A (en) * | 2020-04-21 | 2020-07-24 | 中国商用飞机有限责任公司 | Slat system |
| CN111439390B (en) * | 2020-04-21 | 2021-09-07 | 中国商用飞机有限责任公司 | Slat system |
| CN112373704A (en) * | 2020-11-17 | 2021-02-19 | 中国商用飞机有限责任公司 | System for realizing emergency control of airplane by controlling engine thrust and airplane |
| WO2023035497A1 (en) * | 2021-09-07 | 2023-03-16 | 中国商用飞机有限责任公司 | Fly-by-wire flight backup control system and method |
| CN114560074A (en) * | 2021-12-30 | 2022-05-31 | 中国航空工业集团公司西安飞机设计研究所 | Flap control system and flap control instruction calculation method |
| CN114560074B (en) * | 2021-12-30 | 2024-01-02 | 中国航空工业集团公司西安飞机设计研究所 | Flap control system and flap control instruction calculation method |
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Application publication date: 20170510 |
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