An analytical computation of aircraft’s longitudinal trimmed conditions considering its fuel mass flow rate

The aim of this article is to give simple expressions aircraft’s longitudinal trimmed conditions taking into account the instantaneous fuel mass flow rate, i.e. variation total mass. computation aircraft trim points not a new problem. Nevertheless, current analytical computations are classically performed with constant weight aircraft, hence assuming that rate decrease due has insignificant effects on results. Thus, goal study been assess effect condition and compute correctly “extended conditions” defined as equilibrated in flight considering aircraft. It demonstrated must have an ad-hoc form lead extended conditions. Moreover, do correspond perfect level it case at weight, but present slightly positive path angle leading regular increase altitude. And corrected commands including throttle elevator positions given airspeed altitude computed for compared basic weight. Finally, all verified through numerical simulation twin-engine representative Airbus wide-body family.