Aircraft Landing Control Using the H-inf Control and the Dynamic Inversion Technique

The chapter presents the automatic control of aircraft during landing, taking into account the sensor errors and the wind shears. Both planes—longitudinal and lateral-directional—are treated; the new obtained automatic landing system (ALS) will consists of two subsystems—the first one controls aircraft motion in longitudinal plane, while the second one is for the control of aircraft motion in lateral-directional plane. These two systems can be treated separately, but in the same time, these can be put together to control all the parameters which interfere in the dynamics of aircraft landing. The two new ALSs are designed by using the H-inf control, the dynamic inversion, optimal observers, and reference models. To validate the new obtained ALS, one uses the dynamics associated to the landing of a Boeing 747, software implements the theoretical results and analyzes the accuracy of the results and the precision standards\u27 achievement with respect to the requirements of the Federal Aviation Administration (FAA)

Improved autolanding controller for aircraft encountering unknown actuator failures

The authors have assessed the capability of various neural-aided classical feedback controllers that have been designed for autolanding of a typical modern high performance fighter aircraft under unknown actuator failures and external wind disturbances. Analysis of the fault tolerance envelopes of these neural-aided controllers revealed that position and rate saturation of the healthy actuators resulted in loss of control and failure to complete the autolanding task. Therefore, the over-all fault-tolerance region was not simply connected and exhibited gaps. In this paper we have successfully overcome the problem of gaps in the fault-tolerance envelope of the basic feedback controller by a judicious choice of feedback variables and developing a strategy for optimal gain selection to enlarge the failure tolerance envelopes in the presence of severe winds. The controller is motivated by Nonlinear Dynamic Inversion (NDI) approach and is able to handle six different types of single / double control surface failures. This is achieved by exploiting the full capability of control allocation inherent in the redundant control surfaces. The autolanding controller discussed in this paper is the most robust controller designed so far for the benchmark autolanding problem chosen for study

Aeronautical engineering: A continuing bibliography with indexes (supplement 289)

This bibliography lists 792 reports, articles, and other documents introduced into the NASA scientific and technical information system in Mar. 1993. Subject coverage includes: design, construction and testing of aircraft and aircraft engines; aircraft components, equipment, and systems; ground support systems; and theoretical and applied aspects of aerodynamics and general fluid dynamics