A deployable wing airplane for the exploration of the Martian surface is described and the deploying maneuver in the Martian atmosphere is analyzed. The system could be used to prepare the landing of a human crew on the Martian surface, collecting data on the Martian surface and giving accurate and updated information on the landing site to the astronauts. The crew orbiting the planet releases a balloon containing the aircraft in a stowed wing configuration. The aircraft reaches a stationary velocity in nose-dive trajectory. At a proper altitude from the land the aircraft lifting surfaces deploy, a pull-up maneuver starts, and an horizontal trimmed flight is reached. The parameters which determine the trajectory, such as for example, the initial height, velocity, wing configuration, are selected. A parametric optimization process is here used to evaluate the above mentioned parameters in order to satisfy the final conditions of trimmed-likeflight. Depending on the airplane geometric configuration, a trajectory satisfying the desired requirements can be found. A sensitivity analysis of the final conditions with respect to errors in the optimal parameters is performed, showing that the trajectory is robust and feasible.

A DEPLOYABLE WING AIRPLANE SUPPORTING HUMAN LANDING ON MARTIAN SURFACE / Santoni, Fabio; Gasbarri, Paolo. - STAMPA. - 2:(2003), pp. 785-793. (Intervento presentato al convegno IAC 2003 tenutosi a Bremen, Germany nel Sept.29-Oct.3, 2003).

A DEPLOYABLE WING AIRPLANE SUPPORTING HUMAN LANDING ON MARTIAN SURFACE

SANTONI, Fabio;GASBARRI, Paolo
2003

Abstract

A deployable wing airplane for the exploration of the Martian surface is described and the deploying maneuver in the Martian atmosphere is analyzed. The system could be used to prepare the landing of a human crew on the Martian surface, collecting data on the Martian surface and giving accurate and updated information on the landing site to the astronauts. The crew orbiting the planet releases a balloon containing the aircraft in a stowed wing configuration. The aircraft reaches a stationary velocity in nose-dive trajectory. At a proper altitude from the land the aircraft lifting surfaces deploy, a pull-up maneuver starts, and an horizontal trimmed flight is reached. The parameters which determine the trajectory, such as for example, the initial height, velocity, wing configuration, are selected. A parametric optimization process is here used to evaluate the above mentioned parameters in order to satisfy the final conditions of trimmed-likeflight. Depending on the airplane geometric configuration, a trajectory satisfying the desired requirements can be found. A sensitivity analysis of the final conditions with respect to errors in the optimal parameters is performed, showing that the trajectory is robust and feasible.
2003
IAC 2003
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
A DEPLOYABLE WING AIRPLANE SUPPORTING HUMAN LANDING ON MARTIAN SURFACE / Santoni, Fabio; Gasbarri, Paolo. - STAMPA. - 2:(2003), pp. 785-793. (Intervento presentato al convegno IAC 2003 tenutosi a Bremen, Germany nel Sept.29-Oct.3, 2003).
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/251543
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