A Study of the Landing Approach of STOL Aircraft.

This paper considers the minimum approach distance for landing of STOL aircraft, which is solved by a numerical computation method. Equations of motion use the dynamic model in which aerodynamic coefficients are stated as function of the angle of attack and thrust. Numerical results explain that the optimal minimum approach distance of the landing trajectory has two phases, the dive phase and pull-up phase. The control history of thrust has Bang-Bang type of control by using the minimum value in the dive phase and the maximum value in the pull-up phase. The angle of attack uses the minimum value in the dive phase, but it does not always use the maximum value in the pull-up phase in the case of different optimizing value.