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The article presents the idea of Pitch and Bank Angles estimation with the use of incomplete measurement information. This idea is applied in Attitude and Heading Reference Systems used in the Fly-By-Wire control system for a general aviation aircraft. The idea of the Fly-By-Wire control system for a general aviation aircraft designed in the Department of Avionics and Control Systems is presented in brief. For estimations Lunenberger observers were used. Simulation results are based on the flight test data.

The autonomous control of an aircraft under the flare and touch-down maneuvers is an interesting problem of both theoretical and practical nature. In this paper, a concept of the autonomous landing system (ALS) for unmanned air vehicles (UAV) is presented. The flight control system is addressed to the low-cost, civilian, medium-size UAV with relatively low approach speed and typical nose-wheel landing gear. Final approach is executed automatically using differential GPS guidance system. When the flight control system selects the LANDING option at chosen altitude (based on GPS and pressure altitude), a change in aircraft’s attitude is executed. New attitude ensures safe flare and touchdown of the unmanned aircraft. Flight control system is based on the model-following design technique. Two kinds of flight control systems are taken into consideration.