Monitoring actuator failures for a large transport aircraft – the nominal case
نویسنده
چکیده
Abstract: We consider the problem of designing residual generators with least dynamical orders to solve actuator fault detection and isolation problems for a generic large transport aircraft. The main result of our analysis is the proof of feasibility of the complete isolation of all primary actuator/surface faults in the nominal case by using a minimal number of additional surface angle sensors. The analysis of the nominal case provides residual filter specifications (reference models) to be employed for robust synthesis of residual generators.
منابع مشابه
Robust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input Constraints
The problem of attitude stabilization of a fighter aircraft is investigated in this paper. The practical aspects of a real physical system like existence of external disturbance with unknown upper bound and actuator saturation are considered in the process of controller design of this aircraft. In order to design a robust autopilot in the presence of the actuator saturation, the Composite Nonli...
متن کاملDevelopment of a Detection Scheme for Aircraft Engine Failures Based on the Artificial Immune System Paradigm
A detection scheme based on the artificial immune system (AIS) paradigm was developed for specific classes of aircraft jet engine failures including throttle, burner fuel flow valve, variable nozzle area actuator, variable mixer area actuator, low-pressure spool speed sensor, low-pressure turbine exit static pressure sensor, and mixer pressure ratio sensor. The Modular Aero-Propulsion System Si...
متن کاملAdaptive Failure Compensation for Aircraft Flight Control Using Engine Differentials: Regulation
The problem of using engine thrust differentials to compensate for rudder and aileron failures in aircraft flight control is addressed in this paper in a new framework. A nonlinear aircraft model that incorporates engine differentials in the dynamic equations is employed and linearized to describe the aircraft’s longitudinal and lateral motion. In this model two engine thrusts of an aircraft ca...
متن کاملLinear Quadratic Tracking Design for a Generic Transport Aircraft with Structural Load Constraints
When designing control laws for systems with constraints on the tracking performance, control allocation methods can be utilized. Control allocation methods are used when there are more command inputs than controlled variables. Control allocators can be used to address surface saturation limits, structural load limits, drag reduction constraints, or actuator failures. Most transport aircraft ha...
متن کاملOn the Design of Nonlinear Discrete-Time Adaptive Controller for damaged Airplane
airplane in presence of asymmetric left-wing damaged. Variations of the aerodynamic parameters, mass and moments of inertia, and the center of gravity due to damage are all considered in the nonlinear mathematical modeling. The proposed discrete-time nonlinear MRAC algorithm applies the recursive least square (RLS) algorithm as a parameter estimator as well as the error between the real ...
متن کامل