Robust fault tolerance method of sensor fault of flow control system of aircraft electric fuel pump

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

Inactive Publication Date: 2018-04-20
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

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  • Robust fault tolerance method of sensor fault of flow control system of aircraft electric fuel pump
  • Robust fault tolerance method of sensor fault of flow control system of aircraft electric fuel pump
  • Robust fault tolerance method of sensor fault of flow control system of aircraft electric fuel pump

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Embodiment

[0089] The present invention can be better understood from the following examples. However, those skilled in the art will readily understand that the specific material ratios, process conditions and results described in the examples 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 the electric fuel pump formed by the aviation external meshing gear pump as the working machine, the permanent magnet fault-tolerant motor as the power machine, and the pump and the motor through direct drive mode 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 convert...

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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 systems, and in particular relates to a robust fault-tolerant control method for an aviation electric fuel pump, in particular to a robust fault-tolerant method for sensor faults in a flow control system of an aviation electric fuel pump. Background technique [0002] The multi-electric engine has become an important development direction of aero-engines. The electric fuel pump has become one of the key components of the multi-electric engine due to its simple structure and variable flow rate. Fuel supply plays an important role. [0003] The fuel adjustment range of aero-engine is very wide, and the steady-state and dynamic control performance requirements are high. When designing the 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 flow demand of the engine. However, it is not easy for th...

Claims

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Application Information

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Patent Type & Authority Applications(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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