Simplified loading formulae for pull-out manoeuvres of tailed aeroplanes

Abstract

A method, alternative to that in common use at present, of calculating the response quantities in pull-out manoeuvres relevant to important cases of loads and stresses in aeroplane structures, is presented. The method, based on 'trapezoidal' elevator input, leads to final solutions in the form of closed formulae, which are not only convenient from the computational point of view, but which also permit a comprehensive discussion. It may be used at every stage of design, including the earliest estimates. An important part in all this work is played by 'overshoot factors', and complete charts of these are included. The method can be easily extended to cover asymmetrical manoeuvres.