34 results about "Actuator fault detection" patented technology

The invention discloses an aircraft actuator fault detection and diagnosis method based on a depth random forest algorithm. The method includes: firstly, summarizing the fault mode of an aircraft actuator; establishing an RBF neural network, and collecting the input and output data of the aircraft actuator under the normal working condition to serve as training data, and training the parameters inthe neural network model to obtain analysis redundancy of the monitored actuator; analyzing the residual data of the output signals by collecting the output of the actual actuator and the neural network model, and after the feature extraction, inputting the feature data set into a trained depth random forest multi-classifier for fault mode recognition. According to the invention, the complex nonlinear input and output relation of the aircraft actuator can be accurately simulated by the neural network, the fault mode is accurately recognized by a depth random forest strong classifier, and moreover, the method has the advantages of parallel calculation and high running speed, can be integrated into a flight management computer of an aircraft, realizes the online real-time monitoring, and the accuracy and the efficiency of fault diagnosis of the aircraft actuator are improved.

The invention discloses a dynamic-actuator aircraft attitude distributed type fault-tolerant control system. The system comprises an actuator fault detection and identification unit, an auxiliary system based on an observer and an inversion fault-tolerant control algorithm based on order filtering. According to the distributed type fault-tolerant control system, the actuator fault detection and identification unit is used for obtaining fault information of actuators in real time, the self-adaptive sliding-mode observer is obtained according to an attitude angular speed ring, the observer has strong robustness, an undetermined or interference upper bound does not need to be known, and control surface damage fault information an interference information are both hidden in the observer; a fault-tolerant controller is obtained based on an observer model. Robustness fault-tolerant control over various faults of different types under the multi-fault condition is achieved, the fault-tolerant control system is applied to near-space vehicle attitude stable control and tracking control under the condition of faults of the actuators and the control surface, flying attitude robustness fault-tolerant control is achieved, and good control performance and effect are achieved.

The invention designs an actuator fault detection and identification unit based on multiple observers and a decentralized fault-tolerant control framework for a near space aircraft with disturbances and parameter uncertainty by considering the problem of robust fault-tolerant control after the aircraft has actuator and control surface faults. A system can acquire the fault information of an actuator in real time. A self-adaptive sliding mode observer is designed for an attitude angular velocity loop. A designed observer has strong robustness, does not need to know the upper bound of the uncertainty or the disturbances. The information of a control surface damage fault and the disturbance information are fully implied. A fault-tolerant controller is designed based on an observer model. Through a designed fault-tolerant control system, robust fault-tolerance control is realized under the conditions of various different types of faults and multiple faults. The designed method is respectively applied to posture stabilization control and tracking control of the near space aircraft in the presence of actuator and control surface faults, and flight posture robust fault-tolerant control is realized.

A method in a dual-stage actuator disk drive tests if the secondary actuator has failed while the disk drive is in its normal track-following operating mode. The secondary actuator is removed from the control loop and the primary actuator maintains the read/write head on a data track in the track-following mode. The servo control processor generates a test signal to the secondary actuator and receives the position error signal (PES) as the read head detects the PES bursts in the data track being followed. The servo control processor calculates the response of the secondary actuator to the test signal by deconvolving the motion of the primary actuator from the PES. The calculated response is then compared with an expected response to determine if the secondary actuator has failed. The coherence function can be calculated to measure the statistical validity of the calculated secondary-actuator frequency response.

A dual-stage actuator disk drive uses a secondary-actuator failure-detection and calibration test run by the servo control processor and a relative-position sensor for measuring the position of the secondary actuator relative to its neutral position in response to the calibration test. The secondary-actuator failure detection and calibration test can be performed on a regular schedule or at selected times, such as at disk drive start-up. With the primary actuator biased at a test location, such as a crash stop or a load/unload ramp, the servo control processor generates a test signal to the secondary actuator and receives a relative-position signal (RPS) from the relative-position sensor in response to the test signal. The test comprises two measurements: a measurement of the secondary actuator static characteristics, and a measurement of the secondary actuator dynamic characteristics.

The invention provides a multi-model-based high speed train suspension system multi-actuator fault detection and isolation method. The method involves a first bullet train, a trailer and a second bullet train and comprises the following steps that (1) a suspension system, of a two-bullet-train and one-trailer structure, of a train is modeled to obtain a suspension system model; (2) a fault model is built for each actuator of the suspension system of the two-bullet-train and one-trailer structure; (3) a sliding-mode observer matched with each fault model is arranged based on the corresponding fault model, and the corresponding residual quantity is generated; (4) a fault warning threshold value is generated according to the train operating environment and suspension system working conditions, and a logic controller is used for decision making for all residual quantities to judge whether an alarm needs to be given out or not and point out the fault occurrence position. The application of the fault detection and isolation technology is the effective way for improving the system reliability, and an alarm is given in time when a fault occurs, particularly, the fault occurrence position is pointed out when the multiple actuators break down, and fault screening and system maintenance are facilitated.

An actuator fault detection device that detects a fault of an actuator driven according to a manipulation variable MV output from a controlling device, including: a position acquiring portion that acquires a value of a motor position MP from a detector that detects a position of an actuator corresponding to a manipulation variable MV; a follow-up difference calculating portion that calculates a follow-up difference DM=MV−MP; and an allowable range determining portion that determines whether or not high speed operation or low speed operation of the actuator departs from an allowable range based on a manipulation variable change rate ΔMV, an actuator position change rate ΔMP, and the follow-up difference DM.

For an unmanned aerial vehicle formation system, the invention provides a fault detection method based on an interval observer, and belongs to the technical field of security and reliability. Firstly,when unmanned aerial vehicle formation is in a fault-free state, the interval observer is established based on known bounded disturbance and relative output errors; the fault of an executor is detected through a residual error obtained by output estimation error; compared with the traditional fault detection, a threshold value generator and a residual evaluation function are not required in the fault detection method based on the interval observer; the method in the invention is mainly used for solving the fault detection problem of an unmanned aerial vehicle formation executor, and has relatively low conservative property and relatively high adaptation; the fault detection requirement of the executor can be well satisfied.

The invention relates to an APU air inlet air door actuator fault processing method and device. A connector plug used for butting with a connector socket at a firewall in front of an APU compartment is provided. An APU air inlet air door actuator fault detection and processing method is provided.

The invention discloses a three-connecting-rod manipulator actuator fault detection method based on an event triggering mechanism, which comprises the following steps of firstly, selecting a linearized balance point, and establishing a three-connecting-rod plane manipulator generalized system model by considering actuator fault parameters and external disturbance, establishing a three-connecting-rod plane manipulator fault detection system model according to the three-connecting-rod plane manipulator generalized system model, determining regular, pulse-free and exponential stable conditions of the three-connecting-rod plane manipulator fault detection system model under H-infinity performance, and cooperatively designing the three-connecting-rod plane manipulator fault detection system model based on the stable conditions, and designing a residual error evaluation function and a residual error evaluation threshold value based on the residual error, and giving a fault judgment method. According to the method, the fault of an actuator can be detected in time, safe and reliable operation of a manipulator is guaranteed, limited network bandwidth can be saved, and the method has extremely high practical application value.

The invention discloses a pneumatic actuator fault detection device which is used for detecting the actual fault position of a gate, reducing the troubleshooting time for detecting the fault position and improving the troubleshooting efficiency. The device comprises a piston, a piston rod, a cover plate, a cylinder barrel and a sensor, the cover plates are fixed to the two ends of the cylinder barrel and used for being matched with the cylinder barrel to form a sealed space. The piston is arranged in the cylinder barrel, and the cylinder barrel is used for providing a movement track of the piston; one end of the piston rod is located in the cylinder barrel and connected with the piston, the other end of the piston rod penetrates through the cover plate and is connected with a gate, and the piston is used for driving the gate to move through the piston rod; the sensor is fixed to the outer side of the cylinder barrel and used for sensing the position of the piston.

The present disclosure relates to a vehicle actuator failure detection apparatus and detection method, the vehicle actuator failure detection apparatus comprising: a training device that trains a model using training data including behavior data of a vehicle and a steering compensation angle; and a controller detecting a failure of an actuator in the vehicle based on the model.

The invention discloses a secondary chemical reactor executing mechanism fault detection method based on a function observer. The method comprises the following steps of: firstly, constructing a mathematical model of a system according to the principle of a secondary chemical reactor, and converting the mathematical model into a state equation in a standard form; according to a state equation of the secondary chemical reactor, giving a general form when the secondary chemical reactor has external disturbance and an execution mechanism has a fault; designing a function observer, and giving an error dynamic variance, and a decision logic for judging whether the system breaks down or not; giving a sufficient condition for asymptotic stability of an error dynamic system, and obtaining a fault detection observer parameter according to the sufficient condition; and performing secondary chemical reactor actuator fault detection by using a fault detection observer according to the decision logic. The fault detection method designed in the invention has robustness to unknown input and relatively high sensitivity to faults, does not need to calculate a threshold value, reduces online calculation time, and can complete fault detection of the execution mechanism of the secondary chemical reactor system.