CN102582838B - Control system and control method for operating reverse thrust control and actuation system - Google Patents
Control system and control method for operating reverse thrust control and actuation system Download PDFInfo
- Publication number
- CN102582838B CN102582838B CN201210000209.9A CN201210000209A CN102582838B CN 102582838 B CN102582838 B CN 102582838B CN 201210000209 A CN201210000209 A CN 201210000209A CN 102582838 B CN102582838 B CN 102582838B
- Authority
- CN
- China
- Prior art keywords
- reaction thrust
- control
- switch
- control unit
- micro
- 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.)
- Active
Links
Abstract
The invention provides a control system for operating a reverse thrust control and actuation system. The control system comprises an engine control system connected with a reverse thrust control and actuation system and a plane avionics system; an engine interface control unit connected with the engine control system and the plane avionics system, and connected with the reverse thrust control and actuation system by a distribution contractor; a reverse thrust hood lock; and an accelerator table component including an accelerator rod, a first microswitch and a second microswitch. The first microswitch and the second microswitch are closed or cut off by moving the accelerator rod; the first microswitch and the second microswitch are connected with the engine interface control unit; the first microswitch is connected with the reverse thrust hood lock by a relay. The invention also provides a control method for operating a reverse thrust control and actuation system by the control system, so that the system structure is simplified and the inherent disadvantages of the hydraulic drive reverse thrust device are solved.
Description
Technical field
The present invention relates to a kind of reaction thrust for operating aircraft to control and the control system of actuating system and control method thereof.
Background technology
Airplane reverse thrust controls be used in aircraft landing with actuating system and abort in process and produce deboost.After aircraft landing, airplane reverse thrust controls to launch to block outer culvert air-flow with actuating system start under the instruction of control system, forces outer culvert flow reversal, thus produces reaction thrust.But, control to launch with the accident of actuating system if there occurs airplane reverse thrust in-flight, will the safety hazards of disaster level be caused.
Controlling and the expansion of actuating system and the control of closedown to realize airplane reverse thrust, needing control system reasonable in design.Airplane reverse thrust controls generally to adopt three road instructions with actuating system, and namely three road instructions could realize airplane reverse thrust and control the expansion with actuating system after triggering successively.In prior art, most airplane reverse thrust controls to adopt hydraulic power source to drive with actuating system, the start with actuating system is controlled by the control realization airplane reverse thrust of the servo-hydraulic energy and flow direction thereof, its control system need be realized by the hydraulic tubing of complexity and electric wiring, structure is lengthy and tedious, and maintainability is poor.Under extreme environmental conditions (as microthermal climate), due to the performance degradation that hydraulic power source is intrinsic, airplane reverse thrust controls will obviously to depart from normal performance with the control of actuating system and start process, and this brings adverse influence to aircraft normal flight.In addition, the use of hydraulic oil makes the risk adding combustible liquid leakage in nacelle, adds new requirement to nacelle ventilation discharge opeing and fire prevention system design.
Summary of the invention
The object of the present invention is to provide and a kind ofly realize control system that airplane reverse thrust controls to be controlled by electricity fully with actuating system three road instruction and method thereof, both can realize reaction thrust to control and the expansion of actuating system under three road instructions and closing control, simplify system architecture simultaneously, solve the shortcoming that hydraulic-driven thrust reverser is intrinsic, improve airplane reverse thrust and control the in-use performance with actuating system.
According to a first aspect of the invention, provide a kind of to control, with the control system of actuating system, to comprise for operating reaction thrust:
Engine management system, it controls with described reaction thrust to be connected with actuating system and Aircraft electric system respectively;
Driving engine interface control unit, it is connected with described engine management system and described Aircraft electric system respectively, and is also connected to the control of described reaction thrust and actuating system by distribution contactless switch;
The anti-cover that pushes away is locked, and it controls and actuating system for locking described reaction thrust;
Throttle platform assembly, it comprises throttle lever and the first micro-switch, the second micro-switch, close by mobile described throttle lever or disconnect described first micro-switch and described second micro-switch, described first micro-switch is connected with described driving engine interface control unit respectively with described second micro-switch, and described first micro-switch is also connected to the described anti-cover that pushes away by relay and locks.
Wherein, described distribution contactless switch is also connected with breaker protector.
According to the present invention second aspect, provide a kind of and control, with the control method of actuating system, to comprise step for operating reaction thrust:
A., after aircraft landing, judge reaction thrust controls whether meet unfolding condition with actuating system, and if so, then driving engine interface control unit gives an order one by driving engine interface control unit;
B. when needs use reaction thrust to control with actuating system, carry out closed first micro-switch by mobile throttle lever, order one is delivered to relay, with closed described relay, thus make the anti-cover that pushes away lock energising to unlock;
C. by mobile throttle lever successively closed second micro-switch, the anti-order pushed away of expansion is sent to driving engine interface control unit, described driving engine interface control unit is based on the data message obtained from Aircraft electric system, judge whether to meet imposing a condition of the reaction thrust expansion in driving engine interface control unit, if met, then driving engine interface control unit sends order two to distribution contactless switch, and distribution contactless switch is controlled and actuating system turn-on power to reaction thrust;
D. by the angle signal of engine management system simultaneously monitor command one, order two and throttle lever, and based on the data message obtained from Aircraft electric system, judge whether to meet imposing a condition of the reaction thrust expansion in engine management system, if met, then engine management system sends order three to described reaction thrust control and actuating system, control and actuating system to start described reaction thrust, open the anti-sliding closure that pushes away and produce reaction thrust.
Further, described control method also comprises step:
When e. closing, throttle lever is shifted out reaction thrust position, order one is restored, and power-off locked by the anti-cover that pushes away;
F. by the monitoring of engine management system monitoring Thrust Level Angel, when throttle lever shifts out reaction thrust position, sends the anti-order pushing away closedown to reaction thrust control and actuating system, regain and instead push away sliding closure;
G. when counter push away sliding closure regain completely time, counter push away cover lock automatically latch, engine management system sends instruction by order two recovery to driving engine interface control unit.
Beneficial effect of the present invention:
The three road instructions that the present invention is triggered reaction thrust expansion by throttle platform assembly and closed, the order being achieved three road instructions by equipment such as driving engine interface control units triggers, thus achieves airplane reverse thrust and control to control with the expansion of actuating system and three road instructions of closedown.Owing to present invention employs full electrical equipment, without the need to any hydraulic energy source, thus eliminate the assemblies such as lengthy and tedious hydraulic tubing and valve, and bring benefit for simplied system structure and mitigation system weight.
In addition, use owing to eliminating hydraulic oil, decrease combustible liquid source of leaks potential in nacelle, be beneficial to the discharge opeing of engine installation nacelle and fire protection design.In addition, adopt full electrical equipment to be easy to realize reaction thrust and control the monitoring with the mode of operation of actuating system, thus be beneficial to and improve system maintenance.
Accompanying drawing explanation
Fig. 1 is module diagram, shows and controls a preferred embodiment with the control system of actuating system according to of the present invention for operating reaction thrust.Wherein:
10 reaction thrust control and actuating system
The 20 anti-covers that push away are locked
30 engine management systems
40 distribution contactless switchs
50 driving engine interface control units
60 relays
70 throttle platform assemblies
71 first micro-switchs
72 second micro-switchs
73 throttle levers
80 Aircraft electric systems
90 breaker protectors
Detailed description of the invention
As shown in Figure 1, of the present inventionly control mainly to comprise with the control system of actuating system 10 instead push away that cover locks 20, engine management system 30, distribution contactless switch 40, driving engine interface control unit 50, relay 60 and throttle platform assembly 70 etc. for operating reaction thrust.Reaction thrust control with the Main Function of actuating system 10 be receive aircraft launch counter push away instruction time realize the anti-expansion pushing away sliding closure.
Engine management system (FADEC) 30 1 aspect and reaction thrust control to be connected with actuating system 10, control and actuating system 10 to start reaction thrust for sending order, be connected with Aircraft electric system 80, for obtaining the flying quality of aircraft on the other hand.
Driving engine interface control unit 50 1 aspect is connected with engine management system 30, and for pushing away after closedown completes counter, engine management system 30 sends the anti-signal pushing away closedown to driving engine interface control unit 50, carries out the recovery of order two.Driving engine interface control unit 50 is connected with Aircraft electric system 80, on the other hand for obtaining the flying quality of aircraft.Driving engine interface control unit 50 is also connected to reaction thrust by distribution contactless switch 40 and controls and actuating system 10.
Throttle platform assembly 70 comprises throttle lever 73 and the first micro-switch 71, second micro-switch 72, closed by mobile throttle lever 73 or disconnect the first micro-switch 71 and the second micro-switch 72, first micro-switch 71 is connected with driving engine interface control unit 50 respectively with the second micro-switch 72, and the first micro-switch is also connected to the anti-cover that pushes away by relay 60 and locks 20.Aviator can trigger the closed of two micro-switchs, time phase difference Millisecond by order when moving throttle lever 73.
Wherein, the first and second micro-switchs 71 of driving engine interface control unit 50 and throttle platform assembly 70,72, Aircraft electric system 80 is connected with engine management system 30, for performing setting logic, ensureing that reaction thrust launches to meet and imposing a condition.Driving engine interface control unit 50 adopts its twice instruction controlled of independently passage process.
Distribution contactless switch 40 and relay 60 are electrical equipment, for opening position under default conditions, and the closed conducting realizing power supply after receiving instruction.When reaction thrust controls there is fault with actuating system 10 or prohibit the use, cut off breaker protector 90 by manual mode, realize the anti-cut-out pushing away start power supply, suppress reaction thrust to control the use with actuating system 10.
During operation, throttle lever 73 moves to from throttle lever from ground idle speed and instead pushes away slow train process by aviator, two micro-switchs 71,72 close successively according to set angle, thus jointly realize with driving engine interface control unit 50 triggering in succession controlling the twice instruction that reaction thrust launches.Wherein, one instruction control relay device closes, and to push away cover lock 20 power supply is unlocked to counter, another road instruction controls distribution contactless switch 40 and closes, to control to reaction thrust and actuating system 10 is powered.
Another road instruction that engine management system 30 launches to control for realizing reaction thrust, engine management system 30 is connected with throttle platform assembly 70 with Aircraft electric system 80, driving engine interface control unit 50, software, for performing setting logic, ensures that reaction thrust launches to meet the condition of setting.
Describe in detail below in conjunction with the device shown in Fig. 1 and control, with the method for actuating system, to comprise step for controlling reaction thrust:
A., after aircraft landing, judge reaction thrust controls whether meet unfolding condition with actuating system 10, and if so, then driving engine interface control unit 50 gives an order one by driving engine interface control unit 50;
B. when needs use reaction thrust to control with actuating system 10, carry out closed first micro-switch 71 by mobile throttle lever 73, order one is delivered to relay 60, with closed described relay 60, thus make the anti-cover that pushes away lock 20 energisings to unlock;
C. by mobile throttle lever 73 successively closed second micro-switch 72, the anti-order pushed away of expansion is sent to driving engine interface control unit 50, driving engine interface control unit 50 is based on the data message obtained from Aircraft electric system 80, judge whether to meet imposing a condition of the reaction thrust expansion in driving engine interface control unit 50, if met, then driving engine interface control unit 50 sends order two to distribution contactless switch 40, and distribution contactless switch 40 is controlled and actuating system 10 turn-on power to reaction thrust;
D. by the angle signal of engine management system 30 simultaneously monitor command one, order two and throttle lever, and based on the data message obtained from Aircraft electric system 80, judge whether to meet imposing a condition of the reaction thrust expansion in engine management system 30, if met, then engine management system 30 sends the control of order three to reaction thrust and actuating system 10, control and actuating system to start described reaction thrust, open the anti-sliding closure that pushes away and produce reaction thrust;
When e. closing, throttle lever 73 is shifted out reaction thrust position, order one is restored, and 20 power-off locked by the anti-cover that pushes away;
F. by the angle of engine management system monitoring throttle lever 73, when throttle lever 73 shifts out reaction thrust position, sends the anti-order pushing away closedown and control and actuating system 10 to reaction thrust, regain and instead push away sliding closure;
G. when counter push away sliding closure regain completely time, the anti-cover lock that pushes away 20 latches automatically, and engine management system 30 sends instruction by order two recovery to driving engine interface control unit 50.
Unfolding condition described herein, comprise that reaction thrust controls to launch with the reaction thrust in the unfolding condition of actuating system, driving engine interface control unit impose a condition and reaction thrust in engine management system launches imposes a condition, can be carried out analyzing and setting according to concrete ground contact condition and space velocities by those skilled in the art.
Control system of the present invention and control method thereof jointly realize reaction thrust by the micro-switch of driving engine interface control unit, throttle platform and power plant system control convenience and control and being controlled by electricity fully of actuating system, three road instructions control reaction thrust can be realized control launch with actuating system and close, there is higher level of security.
Described in the present invention, concrete case study on implementation is only better case study on implementation of the present invention, is not used for limiting practical range of the present invention.Namely all equivalences done according to the content of the present patent application the scope of the claims change and modify, and all belong to protection scope of the present invention.
Claims (4)
1. control, with a control system for actuating system, to it is characterized in that, comprising for operating reaction thrust:
Engine management system, it controls with described reaction thrust to be connected with actuating system and Aircraft electric system respectively;
Driving engine interface control unit, it is connected with described engine management system and described Aircraft electric system respectively, and is also connected to the control of described reaction thrust and actuating system by distribution contactless switch;
The anti-cover that pushes away is locked, and it controls and actuating system for locking described reaction thrust;
Throttle platform assembly, it comprises throttle lever and the first micro-switch, the second micro-switch, close by mobile described throttle lever or disconnect described first micro-switch and described second micro-switch, described first micro-switch is connected with described driving engine interface control unit respectively with described second micro-switch, and described first micro-switch is also connected to the described anti-cover that pushes away by relay and locks.
2. control system according to claim 1, is characterized in that, described distribution contactless switch is also connected with breaker protector.
3. control, with a control method for actuating system, to it is characterized in that, comprise step for operating reaction thrust:
A., after aircraft landing, judge reaction thrust controls whether meet unfolding condition with actuating system, and if so, then driving engine interface control unit gives an order one by driving engine interface control unit;
B. when needs use reaction thrust to control with actuating system, carry out closed first micro-switch by mobile throttle lever, order one is delivered to relay, with closed described relay, thus make the anti-cover that pushes away lock energising to unlock;
C. by mobile throttle lever successively closed second micro-switch, the anti-order pushed away of expansion is sent to driving engine interface control unit, described driving engine interface control unit is based on the data message obtained from Aircraft electric system, judge whether to meet imposing a condition of the reaction thrust expansion in driving engine interface control unit, if met, then driving engine interface control unit sends order two to distribution contactless switch, and distribution contactless switch is controlled and actuating system turn-on power to reaction thrust;
D. by the angle signal of engine management system simultaneously monitor command one, order two and throttle lever, and based on the data message obtained from Aircraft electric system, judge whether to meet imposing a condition of the reaction thrust expansion in engine management system, if met, then engine management system sends order three to described reaction thrust control and actuating system, control and actuating system to start described reaction thrust, open the anti-sliding closure that pushes away and produce reaction thrust.
4. control method according to claim 3, is characterized in that, also comprises step:
When e. closing, throttle lever is shifted out reaction thrust position, order one is restored, and power-off locked by the anti-cover that pushes away;
F. by the monitoring of engine management system monitoring Thrust Level Angel, when throttle lever shifts out reaction thrust position, sends the anti-order pushing away closedown to reaction thrust control and actuating system, regain and instead push away sliding closure;
G. when counter push away sliding closure regain completely time, counter push away cover lock automatically latch, engine management system sends instruction by order two recovery to driving engine interface control unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210000209.9A CN102582838B (en) | 2012-01-04 | 2012-01-04 | Control system and control method for operating reverse thrust control and actuation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210000209.9A CN102582838B (en) | 2012-01-04 | 2012-01-04 | Control system and control method for operating reverse thrust control and actuation system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102582838A CN102582838A (en) | 2012-07-18 |
| CN102582838B true CN102582838B (en) | 2015-01-14 |
Family
ID=46472233
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210000209.9A Active CN102582838B (en) | 2012-01-04 | 2012-01-04 | Control system and control method for operating reverse thrust control and actuation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102582838B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2726491C1 (en) * | 2019-09-05 | 2020-07-14 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Control method of gas turbine engine reversible device |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103019224B (en) * | 2012-11-27 | 2015-12-02 | 中国商用飞机有限责任公司 | For the system and method for digital system under test (SUT) dynamic test |
| US10309342B2 (en) | 2015-06-18 | 2019-06-04 | Hamilton Sundstrand Corporation | Actuator control system and method for gas turbine engine |
| CN108679045B (en) * | 2018-04-17 | 2020-04-14 | 中国商用飞机有限责任公司 | Reverse thrust actuation sequence control device of airplane |
| CN111810301B (en) * | 2020-06-08 | 2021-11-05 | 中国航发北京航科发动机控制系统科技有限公司 | Mechanical control safety device for starting and stopping of aircraft engine |
| CN113602507B (en) * | 2021-08-26 | 2022-08-02 | 中国商用飞机有限责任公司 | Automatic reverse control system and method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5960626A (en) * | 1996-11-14 | 1999-10-05 | Societe Hispano Suiza | Electric control system for a turbojet engine thrust reverser including an electromechanical drive device and a locking device which are controlled by an electronic control unit |
| CN101842571A (en) * | 2007-10-31 | 2010-09-22 | 空中客车法国公司 | Control and monitoring system and method |
| CN101946081A (en) * | 2008-02-13 | 2011-01-12 | 埃尔塞乐公司 | System for controlling the cowl of a turbojet engine nacelle thrust reverser |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB201002315D0 (en) * | 2010-02-11 | 2010-03-31 | Goodrich Actuation Systems Ltd | Control system |
-
2012
- 2012-01-04 CN CN201210000209.9A patent/CN102582838B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5960626A (en) * | 1996-11-14 | 1999-10-05 | Societe Hispano Suiza | Electric control system for a turbojet engine thrust reverser including an electromechanical drive device and a locking device which are controlled by an electronic control unit |
| CN101842571A (en) * | 2007-10-31 | 2010-09-22 | 空中客车法国公司 | Control and monitoring system and method |
| CN101946081A (en) * | 2008-02-13 | 2011-01-12 | 埃尔塞乐公司 | System for controlling the cowl of a turbojet engine nacelle thrust reverser |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2726491C1 (en) * | 2019-09-05 | 2020-07-14 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Control method of gas turbine engine reversible device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102582838A (en) | 2012-07-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102582838B (en) | Control system and control method for operating reverse thrust control and actuation system | |
| CN102695868B (en) | Flight control system | |
| RU2398716C2 (en) | Turbojet engine nacelle control system | |
| RU2477380C2 (en) | System and method of control | |
| CN109131901A (en) | The system and method for operation exhausting formula fan propulsion system during aircraft slides | |
| RU2470174C2 (en) | Turbojet nacelle control system | |
| CN104494503A (en) | Comprehensive shelter system of unmanned aerial vehicle | |
| US20110016846A1 (en) | Method and system for controlling at least one actuator of the cowlings of a turbojet engine thrust inverter | |
| CN109131900A (en) | The method of anti-thruster component and operation aircraft for aircraft | |
| EP2920449B1 (en) | Engine and thrust reverser actuation system | |
| CN102395777B (en) | Thrust reversal device | |
| US8684305B2 (en) | Device and method for controlling the power supply of at least one aircraft maintenance actuator | |
| US7210283B2 (en) | Maintenance and inhibition plate for a thrust reverser | |
| CN109188934A (en) | The analogue system and method for avionics system power supply, information data processing terminal | |
| CN110264695B (en) | Navigation light monitoring system and method based on power line carrier communication technology | |
| CN103492676B (en) | 3rd locking assembly of trhrust-reversal device | |
| CN105620770A (en) | Propeller feathering control method | |
| CN206135282U (en) | Xiamen interlocking structure behind cubical switchboard | |
| CN108255149B (en) | Method for remotely clearing faults of unmanned aerial vehicle flight management system | |
| CN102621899B (en) | Method for opening thrust-reversing system of power device of aircraft | |
| Ke et al. | Modeling and simulation of electric thrust reverser actuator control based on simulink | |
| CN217233197U (en) | Safe and reliable aircraft cabin door general control system | |
| US20240043129A1 (en) | Device for controlling an electrical thrust reverser control system for an aircraft | |
| RU2783048C1 (en) | Method for controlling the reverser apparatus of a gas turbine engine | |
| CN113550947A (en) | Stamping turbine 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 | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |