Flight range maximization problem for a simplified aircraft model

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Abstract

The flight range maximization problem for a simplified aircraft model is considered, considering the influence of the amount of fuel on the dynamics of the center of mass. It is assumed that the motion occurs in a vertical plane under the influence of homogeneous gravity forces and homogeneous resistance of the medium. In addition, there are an active thrust force and the ability to change the angle of inclination of the trajectory. These parameters are accepted as controls. An area in the space of initial variables is constructed, for which the problem of optimal synthesis is solved. It is shown that in this area the thrust can be of maximum value, zero value or singular value. The number and consequence of the trajectory arcs with the corresponding thrust have been established.

About the authors

E. V. Malykh

Lomonosov Moscow State University

Author for correspondence.
Email: wyvling@gmail.com
Russian Federation, Moscow

O. Yu. Cherkasov

Lomonosov Moscow State University; Shenzhen MSU-BIT University

Email: oyuche@yandex.ru
Russian Federation, Moscow; Shenzhen, China

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