Author/Authors :
Malaek, S.M sharif university of technology - Department of Aerospace Engineering, تهران, ايران , Marzaabaadi, M.A Aerospace Engineer , Sadati, S.H amirkabir university of technology - Department of Aerospace Engineering, تهران, ايران
Abstract :
A mathematical solution to time-scheduled climb with minimum fuel consumption is presented. The desired final conditions for climb phase are obtained by successive correction of control variables. Aircraft equations of motion are developed based on a point-mass model. The optimality conditions are obtained from Pontryagain s Minimum Principle (PMP). Control variables in the math model consists of the aircraft load factor and its bank angle which both appear in a nonlinear form in the equations of motion, and the throttle setting, which is assumed to vary linearly. Results are computed numerically using Multiple Shooting Method (MSM) and consist of bang-bang control actions for the throttle setting.
