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Three types of actuator faults are considered, namely: the loss of effectiveness fault, the outage fault, and the stuck fault.
Stability is a challenging problem for control system of the hypersonic vehicle when partial loss of effectiveness fault and stuck fault happen on elevators and engine.
By considering some standard assumptions, we propose a robust adaptive fault tolerant protocol for compensating of the actuator bias fault, the partial loss of actuator effectiveness fault, the model uncertainties, and external disturbances.
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The upper bounds of stuck faults, bias faults and loss of effectiveness faults are unknown.
The partial loss of effectiveness faults of elevators and engine are combined in the control gain functions, and Nussbaum approach is introduced to avoid singularity of controllers.
This paper addresses the problem of adaptive fault estimation and fault-tolerant control for a class of nonlinear non-Gaussian stochastic systems subject to time-varying loss of control effectiveness faults.
To illustrate the effectiveness of the proposed adaptive observer, consider loss-of-effectiveness fault model, i.e., the system operates in the normal case before 30 s, and both (u_{1}(t)) and (u_{2}(t)) lose 50% of the effectiveness at 30 s, which means that parameters (theta_{1} ) and (theta_{2}) become −0.5.
Both theoretical analysis and simulations are conducted to evaluate the overall performance of SprintNet and the Forwarding Unit approach with respect to cost-effectiveness, fault-tolerance, system latency, packet loss ratio, aggregate bottleneck throughput, and average path length.
The control method is applied to a helicopter flight control system with loss-in-effectiveness faults.
The bias, drift, and loss of accuracy additive faults are considered along with the loss of effectiveness multiplicative fault.
The feature characteristics directly affect effectiveness of fault recognition.
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