CN102582838B - Control system and control method for operating a thrust control and actuation system - Google Patents

Abstract

The invention provides a control system for operating a thrust reverse control and actuation system, comprising: an engine control system, which is respectively connected with the thrust reverse control and actuation system and an aircraft avionics system; an engine interface control unit, which is respectively connected with the aircraft avionics system The engine control system is connected to the aircraft avionics system, and is also connected to the thrust reverser control and actuation system through the power distribution contactor; The first micro switch and the second micro switch are closed or disconnected by moving the throttle lever. The first micro switch and the second micro switch are respectively connected to the engine interface control unit, and the first micro switch is also connected through The relay is connected to the thrust reverser hood lock. The present invention also provides a control method for operating the thrust reverser control and actuation system by using the above control system, thereby simplifying the system structure and solving the inherent disadvantages of the hydraulic drive thrust reverser.

Description

Control system and control method for operating a thrust reverser control and actuation system

technical field

The invention relates to a control system and a control method for operating a reverse thrust control and actuation system of an aircraft.

Background technique

The aircraft reverse thrust control and actuation system is used to generate reverse thrust during aircraft landing and rejected takeoff. After the aircraft lands, the anti-thrust control and actuation system of the aircraft operates under the command of the control system to block the external airflow and force the external airflow to flow in the opposite direction, thereby generating reverse thrust. However, if the aircraft's anti-thrust control and actuation system is accidentally deployed during flight, it will lead to a catastrophic safety accident.

In order to realize the control of the aircraft reverse thrust control and actuation system opening and closing, it is necessary to design a reasonable control system. The aircraft reverse thrust control and actuation system generally adopts three commands, that is, the deployment of the aircraft reverse thrust control and actuation system can only be realized after the three commands are triggered in sequence. In the prior art, the vast majority of aircraft reverse thrust control and actuation systems are driven by hydraulic sources, and the actuation of the aircraft reverse thrust control and actuation systems is realized through the control of servo hydraulic energy and its flow direction. The hydraulic pipeline and electrical circuit are realized, the structure is complicated, and the maintainability is poor. Under extreme environmental conditions (such as low temperature weather), due to the inherent performance degradation of the hydraulic source, the control and actuation process of the aircraft reverse thrust control and actuation system will obviously deviate from the normal performance, which will adversely affect the normal flight of the aircraft. In addition, the use of hydraulic oil increases the risk of flammable liquid leakage in the nacelle, and adds new requirements to the design of nacelle ventilation and liquid drainage and fire protection systems.

Contents of the invention

The purpose of the present invention is to provide a control system and method for realizing the three-order command all-electric control of the aircraft reverse thrust control and actuation system, which can realize the deployment and closing control of the reverse thrust control and actuation system under the three instructions At the same time, the system structure is simplified, the inherent shortcomings of the hydraulic drive thrust reverser are solved, and the performance of the aircraft thrust reverser control and actuation system is improved.

According to a first aspect of the present invention there is provided a control system for operating a thrust reverser control and actuation system comprising:

An engine control system, which is respectively connected with the thrust reverser control and actuation system and the aircraft avionics system;

An engine interface control unit, which is respectively connected to the engine control system and the aircraft avionics system, and is also connected to the thrust reverser control and actuation system through a power distribution contactor;

a thrust reverser cover lock for locking the thrust reverser control and actuation system;

Throttle console assembly, which includes a throttle lever, a first micro switch, and a second micro switch, the first micro switch and the second micro switch are closed or disconnected by moving the throttle lever, the The first micro switch and the second micro switch are respectively connected to the engine interface control unit, and the first micro switch is also connected to the thrust reverser cover lock through a relay.

Wherein, the power distribution contactor is also connected with a circuit breaker.

According to a second aspect of the present invention, there is provided a control method for operating a thrust reverser control and actuation system, comprising the steps of:

a. After the aircraft lands, judge whether the reverse thrust control and actuation system meets the deployment condition through the engine interface control unit, and if yes, the engine interface control unit issues command 1;

b. When the thrust reverser control and actuation system needs to be used, the first microswitch is closed by moving the throttle lever, and the command one is transmitted to the relay to close the relay, thereby energizing the thrust reverser cover lock for unlocking;

c. By moving the throttle lever and closing the second micro switch in sequence, the engine interface control unit is sent a command to deploy reverse thrust, and the engine interface control unit judges whether the engine interface is satisfied based on the data information obtained from the aircraft avionics system If the setting conditions of reverse thrust deployment in the control unit are satisfied, the engine interface control unit sends command 2 to the power distribution contactor, so that the power distribution contactor turns on the power supply to the reverse thrust control and actuation system;

d. Simultaneously monitor command 1, command 2 and the angle signals of the throttle lever through the engine control system, and based on the data information obtained from the aircraft avionics system, determine whether the setting conditions for reverse thrust deployment in the engine control system are met, If so, the engine control system sends command three to the thrust reverser control and actuation system to activate the thrust reverser control and actuation system to open the thrust reverser sliding cover to generate reverse thrust.

Further, the control method also includes the steps of:

e. When closing, move the throttle stick out of the reverse thrust position, command a reset, and power off the reverse thrust cover lock;

f. Monitor the angle of the throttle lever through the engine control system. When the throttle lever moves out of the reverse thrust position, send the reverse thrust closing command to the reverse thrust control and actuation system, and retract the reverse thrust sliding cover;

g. When the reverse thrust sliding cover is fully retracted, the thrust reverse cover lock is automatically locked, and the engine control system sends an instruction to the engine interface control unit to restore command 2.

Beneficial effects of the present invention:

The invention triggers the three commands of reverse thrust deployment and closure through the accelerator console assembly, and realizes the sequential triggering of the three commands by equipment such as the engine interface control unit, thereby realizing the three directions of deployment and closure of the aircraft reverse thrust control and actuation system Road command control. Since the present invention adopts all-electric equipment, no hydraulic power source is needed, thereby saving complicated components such as hydraulic pipelines and valves, and bringing benefits for simplifying system structure and reducing system weight.

In addition, due to the cancellation of the use of hydraulic oil, the potential source of leakage of flammable liquid in the nacelle is reduced, which is beneficial to the liquid drainage and fire prevention design of the power unit nacelle. In addition, the use of all-electric equipment can easily realize the monitoring of the working status of the reverse thrust control and actuation system, thereby helping to improve the maintainability of the system.

Description of drawings

Fig. 1 is a block diagram illustrating a preferred embodiment of a control system for operating a thrust reverser control and actuation system according to the present invention. in:

10 Anti-thrust control and actuation system

20 reverse thrust hood lock

30 engine control system

40 distribution contactor

50 engine interface control unit

60 relays

70 throttle platform components

71 first micro switch

72 second micro switch

73 Throttle lever

80 aircraft avionics system

90 circuit breaker

Detailed ways

As shown in Figure 1, the control system for operating the thrust reverser control and actuation system 10 of the present invention mainly includes a thrust reverser cover lock 20, an engine control system 30, a power distribution contactor 40, an engine interface control unit 50, and a relay 60 And gas pedal assembly 70 etc. The main function of the thrust reverser control and actuation system 10 is to realize the deployment of the reverse thrust reverser sliding cover when receiving the command to deploy the thrust reverser from the aircraft.

The engine control system (FADEC) 30 is connected with the thrust reverser control and actuation system 10 on the one hand, and is used to send commands to start the thrust reverser control and actuation system 10, and is connected with the aircraft avionics system 80 on the other hand, and is used to obtain aircraft flight data.

On the one hand, the engine interface control unit 50 is connected to the engine control system 30, and is used for sending a signal of reverse thrust shutdown to the engine interface control unit 50 after the reverse thrust shutdown is completed, so as to restore the command 2. On the other hand, the engine interface control unit 50 is connected to the aircraft avionics system 80 for obtaining flight data of the aircraft. The engine interface control unit 50 is also connected to the thrust reverser control and actuation system 10 through the power distribution contactor 40 .

The throttle platform assembly 70 includes a throttle lever 73, a first microswitch 71, and a second microswitch 72. By moving the throttle lever 73, the first microswitch 71 and the second microswitch 72 are closed or disconnected. The dynamic switch 71 and the second microswitch 72 are respectively connected to the engine interface control unit 50 , and the first microswitch is also connected to the reverse thrust cover lock 20 through the relay 60 . When the pilot moves the throttle lever 73, the closing of the two microswitches will be triggered sequentially, with a time difference of milliseconds.

Among them, the engine interface control unit 50 is connected with the first and second microswitches 71, 72 of the throttle console assembly 70, the aircraft avionics system 80 and the engine control system 30, and is used to execute the setting logic to ensure that the anti-thrust deployment meets the set requirements. set conditions. The engine interface control unit 50 uses independent channels to process the two commands it controls.

The power distribution contactor 40 and the relay 60 are electrical devices, which are open by default, and are closed after receiving an instruction to realize the conduction of the power supply. When the anti-thrust control and actuation system 10 is faulty or prohibited to use, the circuit breaker 90 can be cut off manually to cut off the anti-thrust actuation power supply and inhibit the use of the anti-thrust control and actuation system 10 .

During operation, when the pilot moves the throttle lever 73 from ground idle to thrust reverse idle, the two microswitches 71 and 72 are closed sequentially according to the set angle, so as to jointly realize the control of reverse thrust deployment with the engine interface control unit 50 The sequential triggering of the two instructions. Among them, one command controls the closing of the relay device to supply power to the thrust reverser cover lock 20 to unlock it, and the other command controls the closing of the power distribution contactor 40 to supply power to the thrust reverser control and actuation system 10 .

The engine control system 30 is used to implement another instruction for reverse thrust deployment control. The engine control system 30 is connected with the aircraft avionics system 80, the engine interface control unit 50 and the throttle console assembly 70, and the software is used to execute the setting logic to ensure the reverse thrust The expansion meets the set conditions.

The method for controlling the thrust reverser control and actuation system is described in detail below in conjunction with the device shown in FIG. 1 , including steps:

a. After the aircraft lands, it is judged by the engine interface control unit 50 whether the thrust reverser control and actuation system 10 satisfies the deployment condition, and if so, the engine interface control unit 50 issues a command one;

b. When the thrust reverser control and actuation system 10 needs to be used, the first microswitch 71 is closed by moving the throttle lever 73, and the command one is transmitted to the relay 60 to close the relay 60, so that the reverse thrust cover is locked 20 power up to unlock;

c. by moving the throttle lever 73 to close the second microswitch 72 in turn, and send a command to the engine interface control unit 50 to launch reverse thrust, the engine interface control unit 50 is based on the data information obtained from the aircraft avionics system 80, and judges whether to Satisfy the setting condition of reverse thrust deployment in the engine interface control unit 50, if satisfied, the engine interface control unit 50 sends command 2 to the power distribution contactor 40, so that the power distribution contactor 40 sends a reverse thrust control and actuation system 10 Turn on the power supply;

d. Simultaneously monitor the command 1, command 2 and the angle signals of the throttle lever through the engine control system 30, and based on the data information obtained from the aircraft avionics system 80, judge whether the anti-thrust deployment in the engine control system 30 is satisfied. If the conditions are met, the engine control system 30 sends a command 3 to the reverse thrust control and actuation system 10 to start the reverse thrust control and actuation system to open the reverse thrust sliding cover to generate reverse thrust;

e. When closing, move the throttle lever 73 out of the reverse thrust position, command one to restore, and the reverse thrust cover lock 20 is powered off;

f. Monitor the angle of the throttle lever 73 through the engine control system, and when the throttle lever 73 moves out of the reverse thrust position, send a reverse thrust closing command to the reverse thrust control and actuation system 10, and retract the reverse thrust sliding cover;

g. When the reverse thrust sliding cover is fully retracted, the thrust reverse cover lock 20 is automatically locked, and the engine control system 30 sends an instruction to the engine interface control unit 50 to reset the command two.

The deployment conditions described in this article, including the deployment conditions of the reverse thrust control and actuation system, the setting conditions of the reverse thrust deployment in the engine interface control unit, and the setting conditions of the reverse thrust deployment in the engine control system, can be determined by this paper. Those skilled in the art analyze and set according to specific aircraft grounding conditions and airspeed conditions.

The control system and its control method of the present invention realize the anti-thrust control and the all-electric control of the actuation system through the engine interface control unit, the micro switch of the accelerator console and the control equipment of the power plant system, and can realize three-way command control and anti-thrust control Expand and close with actuation system, with a high level of safety.

The specific implementation cases described in the present invention are only preferred implementation cases of the present invention, and are not intended to limit the implementation scope of the present invention. That is, all equivalent changes and modifications made according to the content of the patent scope of the present invention belong to the 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.