Aviation piston engine state fault monitoring and processing method

Abstract

The invention provides an aviation piston engine state fault monitoring and processing method which is applied to an engine numerical control system, and the engine numerical control system is mainly composed of a monitoring sensor, an electronic controller and an execution unit. The method comprises the steps that a monitoring sensor collects signals influencing main parameters of an engine and converts the signals into corresponding electric signals; the electronic controller receives an input signal of the monitoring sensor, and completes state monitoring, fault diagnosis and processing of the engine and set control for operation; the execution unit executes an electronic controller command such that the engine operates according to a predetermined control.

Description

Technical Field

[0001] The present application belongs to the field of aviation power control technology, and specifically relates to a method for monitoring and processing state faults of aviation piston engines. Background Art

[0002] Engine status fault monitoring and processing are implemented by the engine digital control system, which mainly consists of three parts: monitoring sensor, electronic controller and execution unit. The monitoring sensor is used as the input of the digital control system to collect signals that affect the main parameters of the engine (such as oil temperature, oil pressure, cylinder temperature, fuel pressure and intake pressure, etc.) and convert them into corresponding electrical signals. The electronic controller receives the input signal of the monitoring sensor, completes the engine status monitoring fault diagnosis and processing and operates under the established control. The execution unit executes the instructions of the electronic controller so that the engine operates according to the established control.

[0003] Generally speaking, aviation piston engines are rarely used in helicopters at home and abroad. Even if they are used, the currently commonly used engine status monitoring, fault diagnosis and processing cannot meet the needs of helicopters. Summary of the invention

[0004] Purpose of the invention: The present invention uses the engine digital control system to communicate data with the helicopter flight control system through two full-duplex RS-422 interfaces. The engine digital control system and the onboard measurement and control system are not directly connected. The measurement and control system sends instructions related to engine control to the flight control system, and then sends them to the engine digital control system through the flight control system. All communications between the helicopter and the engine digital control system are completed through the flight control system.

[0005] The present application provides a method for monitoring and processing state faults of an aviation piston engine, which is applied to an engine digital control system, wherein the engine digital control system mainly consists of three parts: a monitoring sensor, an electronic controller, and an execution unit; the method includes:

[0006] The monitoring sensor collects signals that affect the main parameters of the engine and converts them into corresponding electrical signals.

[0007] The electronic controller receives input signals from monitoring sensors, completes engine status monitoring, fault diagnosis and processing, and performs predetermined control operations;

[0008] The execution unit executes the electronic controller instructions to make the engine operate according to the established control.

[0009] Preferably, the signals affecting the main parameters of the engine include: oil temperature, oil pressure, cylinder temperature, fuel pressure and intake pressure.

[0010] Preferably, the faults include monitoring sensor faults, execution unit faults and electronic controller faults themselves.

[0011] Preferably, the monitoring sensor faults include sensor short circuit to ground fault, sensor short circuit to power supply fault and sensor open circuit fault; the execution unit faults include stall fault, open circuit fault, drive motor short circuit to ground fault and drive motor open circuit to power supply fault.

[0012] Preferably, the method further comprises:

[0013] Piston engine failures are divided into three levels: I, II, and III, corresponding to critical failures, important failures, and general failures respectively;

[0014] Through fault mechanism analysis, each fault mechanism and the most serious consequence are analyzed, and they are classified into three levels: Ⅰ, Ⅱ, and Ⅲ. At the same time, a combination of two or three faults will lead to the most serious consequences and be classified into three levels: Ⅰ, Ⅱ, and Ⅲ.

[0015] Preferably, the critical fault needs to alert the pilot or operator that the engine has or is about to lose engine power output, or the engine power output is uncontrollable, the engine needs to be shut down manually or automatically, and the aircraft needs to land as soon as possible.

[0016] Preferably, the major fault needs to alert the pilot or operator that part of the engine digital control system has failed, resulting in a reduction in the engine safety margin, a reduction in the engine control accuracy, or a limitation in the maximum output power of the engine;

[0017] Among them, the important faults are further divided into: decreased control quality - the pilot or operator needs to operate the aircraft gently to prevent exceeding the operating limits; decreased power margin - the engine power is limited, and the pilot or operator needs to keep the aircraft in a lower power demand state as much as possible; reduced safety margin - use one or more backup sensors or actuators to control the engine.

[0018] Preferably, the general fault is a failure of a sensor or an actuator unit which does not affect engine control, but only prompts the pilot or operator that there is a fault and requires the ground crew to check the engine and the CNC system after the flight is completed.

[0019] This application has the following technical effects:

[0020] The present invention can achieve safe and reliable engine control, ensure that the helicopter rotation speed fluctuation is small, reduce the burden on operators, and provide timely assistance for handling abnormal situations. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 An embodiment of the present application provides a typical engine digital control system and aircraft interconnection diagram. DETAILED DESCRIPTION

[0022] See also Figure 1 The present invention uses the engine digital control system to communicate data with the helicopter flight control system through two full-duplex RS-422 interfaces. The engine digital control system and the onboard measurement and control system are not directly interconnected. The measurement and control system sends instructions related to engine control to the flight control system, and then sends them to the engine digital control system through the flight control system. All communications between the helicopter and the engine digital control system are completed through the flight control system.

[0023] Monitoring and handling process

[0024] Engine status fault monitoring and processing are realized by the engine digital control system, which mainly consists of three parts: monitoring sensor, electronic controller and execution unit.

[0025] As the input of the CNC system, the monitoring sensor is used to collect signals that affect the main parameters of the engine (such as oil temperature, oil pressure, cylinder temperature, fuel pressure and intake pressure, etc.) and convert them into corresponding electrical signals.

[0026] The electronic controller receives input signals from monitoring sensors, completes engine status monitoring, fault diagnosis and processing, and performs established control operations.

[0027] The execution unit executes the electronic controller instructions to make the engine operate according to the established control.

[0028] Typical engine digital control systems are divided into monitoring sensor failures, execution unit failures, and electronic controller failures. Monitoring sensor failures include sensor short-circuit to ground failures, sensor short-circuit to power failures, and sensor open-circuit failures. Execution unit failures include stall failures, open-circuit failures, drive motor short-circuit to ground failures, and drive motor open-circuit to power failures. There are many types of engine digital control system failures. If all are reported, it will cause a great burden to the pilot or operator.

[0029] The engine state monitoring fault diagnosis and processing logic of the present invention divides piston engine faults into three levels: I, II, and III, which correspond to critical faults, important faults, and general faults, respectively.

[0030] Among them, critical faults need to alert the pilot or operator that the engine may have or is about to lose engine power output, or the engine power output is uncontrollable, and the engine needs to be shut down manually or automatically, and the aircraft needs to land as soon as possible.

[0031] Among them, important faults need to alert the pilot or operator, and some functions of the engine digital control system fail, resulting in reduced engine safety margin, reduced engine control accuracy or limited engine maximum output power, etc.

[0032] Among them, important faults can be further divided into: decreased control quality - the pilot or operator needs to operate the aircraft gently to prevent exceeding the operating limits; decreased power margin - the engine power is limited, and the pilot or operator needs to keep the aircraft in a lower power demand state as much as possible; reduced safety margin - one or more backup sensors or actuator units are used to control the engine. If the backup sensors or actuator units also fail, important faults will occur.

[0033] Among them, the general fault is that some sensors or actuator units fail, which does not affect the engine control, but only prompts the pilot or operator that there is a fault. After the flight is completed, the ground staff must be reminded to check the engine and CNC system.

[0034] The present invention analyzes each fault mechanism and the most serious consequence through fault mechanism analysis, and classifies them into three levels: I, II, and III. At the same time, a combination of two or two faults is analyzed to lead to the most serious consequence, and they are classified into three levels: I, II, and III. For example, if ignition is a double margin, failure of a single ignition mechanism is an important fault, and if all fail, it is a critical fault.

[0035] The present invention simplifies the aircraft warning logic and only needs to send out two warning signals (key fault of the engine digital control system and important fault of the engine digital control system) and one prompt signal (general fault of the engine digital control system).

[0036] Taking a piston engine as an example, typical engine monitoring parameters include throttle position signal, intake air temperature, intake air pressure, speed signal, 4 cylinder head temperatures, 4 cylinder head exhaust temperatures, oil temperature, oil pressure, etc. The pilot or operator needs to pay attention to too many engine monitoring parameters, which puts a great burden on the pilot or operator.

[0037] The present invention simplifies the display of engine monitoring parameters, and sorts out the core parameters according to the logical analysis of the engine monitoring parameter mechanism, and focuses on displaying them, such as speed, cylinder temperature, oil temperature and oil pressure. The key parameters are displayed in color zones, divided into red, yellow and green zones, where the green zone is the normal working range, the yellow zone is the abnormal working state, which does not affect safety for a short time, and the red zone is the abnormal working state that needs to be exited in time. At the same time, when the engine monitoring parameters with red zone alarms enter the red zone, the engine digital control system will send a warning signal.

[0038] Table 1 is a typical engine CNC system alarm signal output

[0039]

[0040] The present invention can achieve safe and reliable engine control, ensure that the helicopter rotation speed fluctuation is small, reduce the burden on operators, and provide timely assistance for handling abnormal situations.

Claims

1. A method for monitoring and handling aircraft piston engine status faults, characterized in that: The method is applied to an engine digital control system, which is mainly composed of a monitoring sensor, an electronic controller and an execution unit; the method includes: The monitoring sensor collects signals that affect the main parameters of the engine and converts them into corresponding electrical signals; The electronic controller receives input signals from monitoring sensors, completes engine status monitoring, fault diagnosis and processing, and performs predetermined control operations; The execution unit executes the electronic controller instructions to make the engine operate according to the established control.

2. The method according to claim 1, characterized in that Signals that affect the main engine parameters include: oil temperature, oil pressure, cylinder temperature, fuel pressure and intake pressure.

3. The method according to claim 2, characterized in that Faults include monitoring sensor failures, actuator unit failures and electronic controller failures themselves.

4. The method according to claim 3, characterized in that: Monitoring sensor faults include sensor short circuit to ground fault, sensor short circuit to power supply fault and sensor open circuit fault; execution unit faults include stall fault, open circuit fault, drive motor short circuit to ground fault and drive motor open circuit to power supply fault.

5. The method according to claim 4, characterized in that The method further comprises: Piston engine failures are divided into three levels: I, II, and III, corresponding to critical failures, important failures, and general failures respectively; Through fault mechanism analysis, each fault mechanism and the most serious consequence are analyzed, and they are classified into three levels: Ⅰ, Ⅱ, and Ⅲ. At the same time, a combination of two or three faults will lead to the most serious consequences and be classified into three levels: Ⅰ, Ⅱ, and Ⅲ.

6. The method according to claim 5, characterized in that The critical faults described above need to alert the pilot or operator that the engine has or is about to lose engine power output, or that the engine power output is uncontrollable, and the engine needs to be shut down manually or automatically, and the aircraft needs to land as soon as possible.

7. The method according to claim 5, characterized in that The above-mentioned major faults need to alert the pilot or operator that some functions of the engine digital control system have failed, resulting in reduced engine safety margin, reduced engine control accuracy or limited engine maximum output power; Among them, the important faults are further divided into: decreased control quality - the pilot or operator needs to operate the aircraft gently to prevent exceeding the operating limits; decreased power margin - the engine power is limited, and the pilot or operator needs to keep the aircraft in a lower power demand state as much as possible; reduced safety margin - use one or more backup sensors or actuators to control the engine.

8. The method according to claim 5, characterized in that The general fault is that the failure of the sensor or actuator unit does not affect the engine control, but only prompts the pilot or operator that there is a fault. After the flight is completed, the ground staff must be reminded to check the engine and CNC system.

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