Aero-engine distributed control system verification method

Abstract

The invention belongs to the field of control system verification, and relates to an aero-engine distributed control system verification method, which comprises the following steps: acquiring an analog quantity signal related to engine control on an engine through a sensor intelligent node, and sending the analog quantity signal to a central controller; the central controller calculates given values according to analog quantity data collected by the sensor intelligent nodes and sends the given values to the execution components, after the execution components control the execution of the terminals, the sensor intelligent nodes collect analog quantity signals again, and the operation is repeated. Technical function verification of a series of multi-electricity distributed control system key technologies such as a multi-electricity distributed system architecture, a distributed control algorithm, a distributed power supply, a distributed bus, a central controller, a data concentrator, an intelligent electric fuel pump and an intelligent execution mechanism is realized. And a certain technical basis and engineering experience are accumulated for a future multi-power distributed control system.

Description

Technical Field

[0001] The present application belongs to the field of control system verification, and in particular relates to a verification method for an aircraft engine distributed control system. Background Art

[0002] Existing aircraft engine control systems all use centralized control systems with centralized architectures. Distributed control systems based on intelligent multi-electric distributed architectures have become the choice for the new generation of aircraft engines due to their high performance, high reliability, high maintainability, high testability, intelligent modules, standard bus interfaces, and low operation and maintenance costs throughout the life cycle. Compared with centralized control systems, distributed control systems are a brand-new architecture with complex interfaces, many new technologies, and high technical risks. In order to promote the maturity of key technologies of distributed control systems, it is necessary to conduct whole-machine verification of this system. Distributed and centralized are two completely different architectural forms. The verification method for centralized control systems cannot meet the verification requirements of related key technologies such as distributed control algorithms, distributed power supplies, distributed buses, central controllers, data concentrators, intelligent electric fuel pumps, and intelligent actuators of distributed control systems. There is currently no verification method for aircraft engine distributed control systems. Summary of the invention

[0003] The purpose of this application is to provide a method for verifying an aircraft engine distributed control system to solve the problem that distributed control system verification cannot be achieved in the prior art.

[0004] The technical solution of the present application is: a method for verifying an aircraft engine distributed control system, comprising:

[0005] The analog signals related to engine control on the engine are collected through the sensor intelligent node and sent to the central controller;

[0006] The central controller calculates the main fuel set value, the fuel set value of all geometric section control loops of the engine, the nozzle set value and the set values ​​of other geometric sections according to the analog data collected by the sensor intelligent node, and publishes the main fuel set value and the fuel set value of all geometric section control loops of the engine to the distributed bus; transmits the nozzle set value and the set values ​​of other geometric sections to the centralized digital electronic controller, and the centralized digital electronic controller realizes the loop control of the nozzle and other geometric sections;

[0007] The fuel electric fuel pump obtains the fuel set value from the distributed bus, and performs the acquisition, closed-loop control, fault diagnosis and processing of the main fuel-related signals;

[0008] The servo electric fuel pump obtains the fuel volume required by the servo system and the boost demand at the outlet after the pump from the distributed bus, and then controls the motor speed inside the servo electric fuel pump; at the same time, the servo intelligent node receives the given value of the geometric section issued by the central controller through the secondary bus of the distributed bus, and performs specific control of the geometric section inside the engine;

[0009] The sensor intelligent node again collects analog signals such as speed, temperature, pressure, etc. related to engine control and sends them to the central controller. The central controller recalculates the main fuel set value, the fuel set value of all geometric section control loops of the engine, the nozzle set value and the set values ​​of other geometric sections based on the current analog signals, and repeats this process to achieve continuous distributed verification.

[0010] Preferably, when the control system fails, the main fuel electric fuel pump receives the bench command through serial port communication to complete the open-loop control of the fuel flow or the fuel cut-off process.

[0011] Preferably, a parking solenoid valve is provided on the main fuel electric fuel pump. When the main fuel electric fuel pump diagnoses TTP / C bus or central controller fault information, the test bench serial port communication mode is set, the PLA instruction is received, and the main fuel open-loop regulation plan is controlled to manually stop the engine.

[0012] Preferably, when the central controller detects engine surging, the internal control software determines the oil cut timing, and the main fuel electric fuel pump executes the parking solenoid valve disconnection or connection instruction to control the parking solenoid valve to work according to the oil cut timing to achieve oil cut when surging.

[0013] Preferably, the central controller is also provided with a fault judgment module, in which corresponding standard given values ​​are stored for different analog signals. When the servo electric fuel pump, the main fuel electric fuel pump and the mechanical structure of the engine receive the given values, the fed-back analog signal is compared with the standard given values ​​respectively. When the difference between the fed-back analog signal and the standard given value exceeds the set threshold, the specific fault of the corresponding component is determined.

[0014] Preferably, the specific control of the geometric cross-section inside the engine includes sensor signal acquisition, position closed-loop control, fault diagnosis and processing.

[0015] The aviation engine distributed control system verification method of the present application realizes the technical function verification of a series of key technologies of multi-electric distributed control systems, such as multi-electric distributed system architecture, distributed control algorithm, distributed power supply, distributed bus, central controller, data concentrator, intelligent electric fuel pump, and intelligent actuator, and accumulates a certain technical foundation and engineering experience for future multi-electric distributed control systems. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0017] Figure 1 This is a schematic diagram of the overall structure of this application. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] A verification method for aircraft engine distributed control systems, based on the evaluation results of distributed control system verification risks, redistributes and tailors the engine control system functions, and conducts comprehensive verification of a series of key technologies of multi-electric distributed control systems such as multi-point distributed system architecture, distributed control algorithm, distributed power supply, distributed bus, central controller, data concentrator, intelligent electric fuel pump, and intelligent actuator.

[0020] The system adopts a verification solution that combines centralized and distributed architectures. Figure 1 As shown, the key technologies of the distributed control system that need to be verified include the central controller, sensor intelligent node, main fuel electric fuel pump, servo electric fuel pump, servo intelligent node and distributed bus connecting distributed intelligent nodes. The rest is the centralized control system technology, including fuel boost pump, test bench, test bench 270VDC power supply, fuel actuator, nozzle control device and centralized digital electronic controller. The rest is the mechanical structure of the engine.

[0021] The steps include:

[0022] Step S100, collecting analog signals such as speed, temperature, pressure, etc. on the engine related to engine control through the sensor intelligent node, and sending them to the central controller;

[0023] Step S200: The central controller calculates the main fuel set value, the fuel set value of the engine's entire geometric section control loop, the nozzle set value, and the set values ​​of the remaining geometric sections based on the analog data collected by the sensor intelligent node, and publishes the main fuel set value and the fuel set value of the engine's entire geometric section control loop to the distributed bus; the nozzle set value and the set values ​​of the remaining geometric sections are transmitted to the centralized digital electronic controller, and the centralized digital electronic controller implements the loop control of the nozzle and the remaining geometric sections. The feedback values ​​of the nozzle and the remaining geometric sections are collected by the centralized digital electronic controller, and the status of the nozzle and the remaining geometric sections is monitored.

[0024] Step S300, the main fuel electric fuel pump obtains the fuel set value from the distributed bus, and performs main fuel related signal collection, closed-loop control, fault diagnosis and processing.

[0025] Preferably, in order to ensure the safety of the ground test bench verification of the distributed control system: a parking solenoid valve is set on the main fuel electric fuel pump to realize the parking, anti-gasping, over-speed protection functions, fault self-diagnosis and processing functions. When the main fuel electric fuel pump diagnoses the TTP / C bus or central controller fault information, the test bench serial port communication mode is set to receive the PLA (or parking switch) command, and the main fuel open-loop regulation plan is controlled to manually realize the engine shutdown.

[0026] Specifically, when the control system fails, the main fuel electric fuel pump receives the bench command through the serial communication to complete the open-loop control of the fuel flow or the fuel cut-off process. When the central controller detects engine surge, the internal control software determines the oil cut-off sequence, and the main fuel electric fuel pump executes the parking solenoid valve disconnection or connection command to control the parking solenoid valve to work according to the oil cut-off sequence, thereby achieving the purpose of eliminating surge and cutting oil.

[0027] Step S400, the servo electric fuel pump obtains the fuel quantity required by the servo system and the boost demand at the outlet after the pump from the distributed bus, and then controls the motor speed inside the servo electric fuel pump to achieve the adjustment of the adjustable geometric oil source.

[0028] At the same time, the servo intelligent node receives the given value of the geometric section issued by the central controller through the secondary bus of the distributed bus, and performs specific control of the geometric section inside the engine, including sensor signal acquisition, position closed-loop control, fault diagnosis and processing.

[0029] In step S500, the sensor intelligent node collects analog signals such as speed, temperature, pressure, etc. related to engine control again and sends them to the central controller. The central controller recalculates the main fuel set value, the fuel set value of all geometric section control loops of the engine, the nozzle set value and the set values ​​of other geometric sections according to the current analog signals, and repeats this process to achieve continuous distributed verification.

[0030] Preferably, a fault judgment module is also provided in the central controller, and corresponding standard given values ​​are stored in the fault judgment module for different analog signals, such as speed given values, temperature given values, etc. When the servo electric fuel pump, the main fuel electric fuel pump and the mechanical structure of the engine receive the given values, the feedback analog signal is compared with the standard given values ​​respectively. When the difference between the feedback analog signal and the standard given value exceeds the set threshold, the specific fault of the corresponding component is determined, and the specific fault includes surge, guide vane breakage, etc., thereby realizing the verification of each component.

[0031] The geometric section controlled by the servo intelligent node should follow the principle that the engine safety will not be affected when the control is abnormal.

[0032] The functions of the distributed solution are decomposed into multiple intelligent nodes for collaborative completion, which puts forward higher requirements on the bandwidth, transmission distance and reliability of the bus. Limited by the bandwidth and transmission distance of the primary bus of the distributed control system, the distributed bus adopts a primary + secondary network structure during bench verification. The primary network adopts a high-bandwidth and high-fault-tolerant bus, and the secondary network adopts a low-speed and high-fault-tolerant bus. Research and verification of distributed bus topology technology based on time triggering are carried out.

[0033] Through the above design, the technical function verification of a series of key technologies of multi-electric distributed control systems such as multi-electric distributed system architecture, distributed control algorithm, distributed power supply, distributed bus, central controller, data concentrator, intelligent electric fuel pump, and intelligent actuator has been realized, accumulating a certain technical foundation and engineering experience for future multi-electric distributed control systems.

[0034] Finally, it should be noted that: the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0035] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for verifying an aircraft engine distributed control system, characterized in that: include: The analog signals related to engine control on the engine are collected through the sensor intelligent node and sent to the central controller; The central controller calculates the main fuel set value, the fuel set value of all geometric section control loops of the engine, the nozzle set value and the set values ​​of other geometric sections according to the analog data collected by the sensor intelligent node, and publishes the main fuel set value and the fuel set value of all geometric section control loops of the engine to the distributed bus; transmits the nozzle set value and the set values ​​of other geometric sections to the centralized digital electronic controller, and the centralized digital electronic controller realizes the loop control of the nozzle and other geometric sections; The fuel electric fuel pump obtains the fuel set value from the distributed bus, and performs the acquisition, closed-loop control, fault diagnosis and processing of the main fuel-related signals; The servo electric fuel pump obtains the fuel volume required by the servo system and the boost demand at the outlet after the pump from the distributed bus, and then controls the motor speed inside the servo electric fuel pump; at the same time, the servo intelligent node receives the given value of the geometric section issued by the central controller through the secondary bus of the distributed bus, and performs specific control of the geometric section inside the engine; The sensor intelligent node again collects analog signals such as speed, temperature, pressure, etc. related to engine control and sends them to the central controller. The central controller recalculates the main fuel set value, the fuel set value of all geometric section control loops of the engine, the nozzle set value and the set values ​​of other geometric sections based on the current analog signals, and repeats this process to achieve continuous distributed verification.

2. The aircraft engine distributed control system verification method according to claim 1, characterized in that: When the control system fails, the main fuel electric fuel pump receives the test bench command through serial communication to complete the open-loop control of the fuel flow or fuel cut-off processing.

3. The aircraft engine distributed control system verification method according to claim 1, characterized in that: A parking solenoid valve is arranged on the main fuel electric fuel pump. When the main fuel electric fuel pump diagnoses TTP / C bus or central controller fault information, the test bench serial port communication mode is set, the PLA instruction is received, and the main fuel open-loop regulation plan is controlled to manually stop the engine.

4. The aircraft engine distributed control system verification method according to claim 3, characterized in that: When the central controller detects engine surging, the internal control software determines the oil cut-off sequence, and the main fuel electric fuel pump executes the parking solenoid valve disconnection or connection command to control the parking solenoid valve to work according to the oil cut-off sequence to eliminate surging and cut oil.

5. The aircraft engine distributed control system verification method according to claim 1, characterized in that: The central controller is also provided with a fault judgment module, which stores corresponding standard given values ​​for different analog signals. When the servo electric fuel pump, the main fuel electric fuel pump and the mechanical structure of the engine receive the given values, the fed-back analog signal is compared with the standard given values ​​respectively. When the difference between the fed-back analog signal and the standard given value exceeds the set threshold, the specific fault of the corresponding component is determined.

6. The aircraft engine distributed control system verification method according to claim 1, characterized in that: The specific control of the geometric cross-section inside the engine includes sensor signal acquisition, position closed-loop control, fault diagnosis and processing.

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