Automatische, schublose Landung eines Flugzeuges großer Streckung unter Verwendung der Bremsklappen und mit variablen Gleitpfadwinkeln

In this thesis a special landing procedure and the associated flight control functions are described that allow full automatic landings without using the thrust. While in existing automatic landings thrust is required, the here presented method corresponds with an automatic landing of a glider. Compared to existing automatic landing methods, in which a glide slope with a constant glide slope angle is used, the glide slope angle and the glide slope are here l adapted to the prevailing wind conditions. It is adjusted in that way, that the approach along the glide slope can be done without thrust. Instead of using the thrust, the airbrakes in combination with the elevator are used as control elements to control the longitudinal motion of the aircraft. At landing approaches without wind the used glide slope is already relative steep. At headwind conditions it becomes steeper, at tailwind it flattens. Due to continuous changing wind conditions it becomes bended. The functions and algorithms are described for the longitudinal motion of the aircraft and for the individual phases of the automatic landing: for the approach towards the glide slope, the approach along the glide slope and the flare. Without thrust the approach towards the glide slope is done by using the best glide speed. This is calculated by using the wind speed, which is calculated in the flight control functions. Then the aircraft sinks to the runway along an adapted glide slope, as described above. During the flare the height and the air speed are controlled at the same time. For the vertical flare path time dependent algorithms and algorithms depending on the distance to the runway threshold are compared. Afterwards a time dependent flare algorithm is elected. For the control of the longitudinal motion of the aircraft the TECS (Total Energy Control System) is used. It was introduced in [Lam83]. Here it is modified and extended. Extensions are among other things the control of the airbrakes and the compensation of the lift changing, which occurs as a result of airbrake deflections. The modified TECS is used in all phases of the landing, especially also during the flare to control the vertical path and the air speed at the same time by using the airbrakes in combination with the elevator. The presented flight control functions are a part of a complete flight control system, which was developed in the project LAPAZ2 for the demonstrator aircraft STEMME S15 of the company Stemme. They have been successfully tested and validated in simulations and in test flights. Based on these results the controlled behavior of the aircraft is presented and discussed.