An entry, descent, and flight (EDF) trajectory profile for a Mars airplane mission is defined as consisting of the following elements: ballistic entry of an aeroshell; supersonic deployment of a decelerator parachute; subsonic release of a heat shield; release, unfolding, and orientation of an airplane to flight attitude; and execution of a pull up maneuver to achieve trimmed, horizontal flight. Using the Program to Optimize Simulated Trajectories (POST) a trajectory optimization problem was formulated. Model data representative of a specific Mars airplane configuration, current models of the Mars surface topography and atmosphere, and current estimates of the interplanetary trajectory, were incorporated into the analysis. The goal is to develop an EDF trajectory to maximize the surface-relative altitude of the airplane at the end of a pull up maneuver, while subject to the mission design constraints. The trajectory performance was evaluated for three potential mission sites and was found to be site-sensitive. The trajectory performance, examined for sensitivity to a number of design and constraint variables, was found to be most sensitive to airplane mass, aerodynamic performance characteristics, and the pull up Mach constraint. Based on the results of this sensitivity study, an airplane-drag optimized trajectory was developed that showed a significant performance improvement.
Development of a Mars Airplane Entry, Descent, and Flight Trajectory
2001
22 pages
Report
No indication
English
Astronomy & Astrophysics , Extraterrestrial Exploration , Mars missions , Descent trajectories , Aircraft design , Atmospheric entry , Aircraft performance , Design analysis , Interplanetary trajectories , Mission planning , Trajectory optimization , Flight mechanics , Aeroshells , Parachutes , Heat shielding , Aerodynamic balance , Aerodynamic drag , Attitude(Inclination) , Aircraft models , Mars probes
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