Numerical study on Longitudinal control of Cessna 172 Skyhawk aircraft by Tail arm length

Abstract

This paper covers a new method of longitudinally controlling an aircraft by changing the horizontal tail arm length, without the conventional control surface called 'elevator'. The effects of changing horizontal tail arm length from its steady level trimmed condition are determined numerically for the chosen Cessna aircraft. From the numerical calculations, the possibilities of implementing this type of control in the chosen Cessna aircraft are analyzed. At last, some recommendations are suggested for the effective longitudinal control of the Cessna aircraft by changing horizontal tail arm length. Further, it is also suggested that employing both elevator control and tail arm length control together will make an aircraft to meet any kind of longitudinal controllability and stability requirement at any instant. This optimal aircraft configuration can be achieved by proposing a novel configuration and morphing solutions.