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Robust Fault Tolerance Method for Sensor Faults in Aircraft Electric Fuel Pump Flow Control System

A technology for electric fuel pump and sensor failure, which is applied in the field of control system capacity

Inactive Publication Date: 2019-11-12
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0013] It can be seen that the research on fault-tolerant control based on sliding mode theory has received a lot of attention and obtained a lot of research results, including fault-tolerant control methods for sensor faults

Method used

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  • Robust Fault Tolerance Method for Sensor Faults in Aircraft Electric Fuel Pump Flow Control System
  • Robust Fault Tolerance Method for Sensor Faults in Aircraft Electric Fuel Pump Flow Control System
  • Robust Fault Tolerance Method for Sensor Faults in Aircraft Electric Fuel Pump Flow Control System

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Embodiment

[0089] According to the following examples, the present invention can be better understood. However, those skilled in the art can easily understand that the specific material ratios, process conditions and results described in the embodiments are only used to illustrate the present invention, and should not and will not limit the present invention described in detail in the claims. .

[0090] The present invention takes an electric fuel pump with an aviation external gear pump as a working machine, a permanent magnet fault-tolerant motor as a power machine, and a direct drive connection between the pump and the motor as the specific research object. figure 2 The embodiment shown.

[0091] The specific instructions are as follows:

[0092] (1) Basic principle analysis of aviation electric fuel pump flow control system

[0093] The aviation electric fuel pump flow control system involved in this patent is mainly composed of an electric fuel pump controller, a power converter, a motor,...

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Abstract

The invention discloses a robust fault tolerance method of a sensor fault of a flow control system of an aircraft electric fuel pump. A rotating speed instruction adjustment part and a rotating speedcontrol part are arranged. The rotating speed instruction adjustment part provides a proper electric fuel pump rotating speed instruction suitable for an all flow range for the control system based onan engine fuel demand instruction, a fuel flow non-linear steady-state model and an output fuel flow of an electric fuel pump. The rotating speed control part is mainly used for minimizing an error between an actual rotating speed and a rotating speed instruction; and under the circumstance that the uncertainty and the sensor failure are considered, on the basis of an adaptive combined nonlineardynamic model of the electric fuel pump, a sliding mode fault estimator and a sliding mode rotating speed controller are designed comprehensively based on a sliding mode theory, so that the rotating speed response of the electric fuel pump is done quickly and the expected rotating speed is reached accurately; and thus on-demand oil supply for the aero-engine by the electric fuel pump is realized safely, reliably, quickly, and precisely.

Description

Technical field [0001] The invention belongs to the technical field of control system tolerance, and specifically relates to a robust fault-tolerant control method for aviation electric fuel pumps, in particular to a robust fault-tolerant method for sensor failures of aviation electric fuel pump flow control systems. Background technique [0002] Multi-electric engines have become an important development direction of aero-engines. Electric fuel pumps have become one of the key components of multi-electric engines due to their simple structure and variable flow. The electric fuel pump fuel flow control system can provide the engine on demand. Fuel supply plays an important role. [0003] Aviation engines have a wide range of fuel adjustment and high steady-state and dynamic control performance requirements. When designing an electric fuel pump flow control system, it is necessary to ensure that the fuel flow has the specified steady-state accuracy and dynamic accuracy under each fl...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04G05B17/02
CPCG05B13/04G05B17/02
Inventor 肖玲斐丁润泽陈玉升叶志锋金霞申斌
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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