Download A fault tolerant flight control system for sensor and by M. R. Napolitano, Y. An, B. Seanor PDF

By M. R. Napolitano, Y. An, B. Seanor

Plane layout three (2000) 103 - 128

In contemporary years neural networks were proposed for identity and keep watch over of linear and non-linear dynamic platforms. This paper describes the functionality of a neural network-based fault-tolerant method inside a flight keep watch over procedure. This fault-tolerant flight keep watch over approach integrates sensor and actuator failure detection, identity, and lodging (SFDIA and AFDIA). the 1st job is completed via incorporating a primary neural community (MNN) and a suite of n decentralized neural networks (DNNs) to create a process with n sensors which has the facility to become aware of a large choice of sensor mess ups. the second one scheme implements an analogous major neural community built-in with 3 neural community controllers. The contribution of this paper makes a speciality of improvements of the SFDIA scheme to permit the dealing with of sentimental mess ups in addition to addressing the problem of integrating the SFDIA and the AFDIA schemes with out degradation of functionality by way of fake alarm charges and improper failure identi"cation. the result of the simulation with various actuator and sensor mess ups with a non-linear plane version are offered and mentioned.

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Additional info for A fault tolerant flight control system for sensor and actuator failures using neural networks

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This difference in lift would cause the helicopter to be uncontrollable in any situation other than hovering in a calm wind. There must be a means of compensating, correcting, or eliminating this unequal lift to attain symmetry of lift. When the helicopter moves through the air, the relative airflow through the main rotor disk is different on the advancing side than on the retreating side. The relative wind encountered by the advancing blade is increased by the forward speed of the helicopter, while the relative wind speed acting on the retreating blade is reduced by the helicopter’s forward airspeed.

The retreating blade angle Downward movement response here Upward force applied here C Forward B A Downward force applied here D Upward movement Figure 2-28. Gyroscopic precession. of incidence is increased and the advancing blade angle of incidence is decreased resulting in a tipping forward of the tip-path plane, since maximum deflection takes place 90° later when the blades are at the rear and front, respectively. Angle of attack decreased Maximum upward deflection Blade rotation Maximum downward deflection ct re Di ion of l tr e av Blade rotation Angle of attack increased Figure 2-29.

This same control movement simultaneously decreases the angle of incidence of the other blade the same amount, thus decreasing the lifting force applied at that point in the plane of rotation. The blade with the increased angle of incidence tends to flap up; the blade with the decreased angle of incidence tends to flap down. Because the rotor disk acts like a gyro, the blades reach maximum deflection at a point approximately 90° later in the plane of rotation. Figure 2-29 illustrates the result of a forward cyclic input.

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