J. Rosenow, H. Fricke

Along the ambitious SESAR objectives, new aircraft performance models are necessary to calculate and optimize free route aircraft specific trajectories considering real weather conditions. Here, an aircraft performance model is presented, which meets these requirements. To consider constant changes in speed and acceleration, the dynamic equation of this unsteady system is solved analytically. Free variables are controlled by an aircraft specific proportional plus integral plus derivative controller. Therewith, the model is based solely on physical functions (except for the drag polar, which is approximated by BADA) and calculates only physically possible trajectories. Several aircraft and engine types are included, the aircraft specific behavior can be modeled in detail and emissions can be quantified. Trajectory optimization is demonstrated by a variation of the cruising altitude and the target speed. Both are effective variables. We found, that the developed optimization target function cannot be generalized for all aircraft types, especially not under real weather conditions. Individual aircraft specific target functions mainly depend on the drag polar, the maximum Mach number and the operating empty weight.

Deutscher Luft- und Raumfahrtkongress 2016, Braunschweig

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2016

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

urn:nbn:de:101:1-2016102111139

Flugleistung, Trajektorienoptimierung

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21.10.2016