Redundancy design method of fault diagnosis of flight control system

A flight control system and fault diagnosis technology, applied in the direction of electrical testing/monitoring, etc., can solve the problems of not being able to be used for diagnosis, poor anti-interference ability, insensitive to slowly changing faults, etc., so as to reduce the probability of fault misjudgment, The effect of system reliability assurance

Active Publication Date: 2019-05-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The basic Kalman filter is greatly affected by the mismatch and disturbance of the actual system model, and it is easy to diverge. This method c

Method used

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  • Redundancy design method of fault diagnosis of flight control system
  • Redundancy design method of fault diagnosis of flight control system
  • Redundancy design method of fault diagnosis of flight control system

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Embodiment 1

[0042] The redundant design method of the flight control system fault diagnosis provided by the present invention simplifies the system model by equivalently processing the sensor fault model, and takes the simplified model as the object to design the extended Kalman filter, which can improve the system status. Perform joint estimation with sensor fault parameters. In order to improve the stability of the filter and the estimation accuracy and tracking speed of sensor fault parameters, the noise variance in the filtering algorithm is appropriately increased, and the estimation results are processed by wavelet filtering to obtain a smoother According to the estimated value of the output value, it can quickly detect whether the sensor is malfunctioning or not.

[0043] The invention is based on the hardware redundancy of the flight control system. The system includes a power supply module, a CPU control unit and a bus module. Each module is independent of each other and does not int...

Embodiment 2

[0064] The flight control computer of the drone is equipped with three control units. The IDs of the three control units are respectively defined as CU-A, CU-B and CU-C. The three control units work at the same time after the flight control computer is powered on. The default CU-A is the master control unit, and the other two are slave control units. The order of priority of control rights is CU-A, CU-B and CU-C from high to low. The three control units simultaneously receive the input information transmitted by the interface unit through the internal bus of the system, such as the angle of attack sensor information. After completing the calculation and processing of navigation and control, the main control unit outputs corresponding control information to the interface unit. At the same time, the three control units also detect the fault status of each control unit in real time through self-inspection and mutual inspection. When the main control unit fails, the first slave con...

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Abstract

The invention discloses a redundancy design method of fault diagnosis of a flight control system. According to the method, equivalence is carried out on a sensor fault model, a system model is simplified, an extended Kalman filter is designed by taking the simplified model as an object, the systems state and sensor fault parameters are estimated in a combined way, a noise variance in a filtering algorithm is increased properly to improve the stability of the filter and the estimation precision and tracking speed for the sensor fault parameters, wavelet filtering is carried out on an estimationresult to obtain a relatively smooth estimated value, and whether a fault occurs in the sensor can be detected rapidly according to an output value. The system stability is ensured, a fault can be determined rapidly and accurately, and the possibility of fault misjudgment can be reduced.

Description

Technical field [0001] The invention belongs to the failure diagnosis and application of a flight control system, and specifically relates to a redundant design method for the failure diagnosis of a flight control system. Background technique [0002] The flight control computer is the core part of the flight control system, which can improve the reliability of the system from both hardware and software. The hardware adopts fault avoidance technology to improve and perfect the quality and reliability of the components itself; the software adopts fault tolerance technology, through the organization and allocation of system resources, designing system fault detection and diagnosis, fault handling and recovery and other management strategies to improve software fault tolerance ability. [0003] Sensor fault diagnosis is generally based on online analytical models, using ARMA model, neural network, wavelet neural network to predict the output time series of the sensor, and the predict...

Claims

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Application Information

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IPC IPC(8): G05B23/02
Inventor 陈欣谈娟
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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