Trajectory Analysis and Design for Planetary Powered Descent and Orbital Ascent Maneuvers

Date
2019
Authors
Onishi, Melissa
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Azimov, Dilmurat
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Mechanical Engineering
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NASA’s past Mars missions such as Mars Pathfinder, the Mars Exploration Rovers and the Mars Science Laboratory projects have led to the necessity of designing the next generation of landers, one of the goals of which is to achieve safe, velocity of less than 1 m/s and precise landing, within 100 m from the designated landing site. Previous studies focused on the formulation of manifolds of initial and final points for atmospheric entry, powered descent and landing. These manifolds can be generated by a construction of envelopes of the maneuver trajectories using a vast range of terminal conditions for the trajectory and lander’s parameters. This paper describes the design, analysis and construction of trajectory envelopes for accurate landing maneuvers. A family of envelopes is generated by varying a vast range of terminal conditions to satisfy the proposed design space based on previous Mars missions. The following phases are considered in the landing maneuvers: exoatmospheric thrust phase, atmospheric transit phase and powered descent and landing phase. The entry velocity components were compared in two cases where the velocity component in the y-direction, vy0 is zero or a nonzero constant with several fixed conditions to analyze the overall profile of the entry trajectory. From case B, where vy0 is a nonzero constant, one of the trajectories achieved a landing altitude of 0.3891 m, velocity of 0.0015 m/s and distance of 88. 02559 m from the designated landing site. Specific parameters are designated to satisfy the proposed design space and achieve accurate landing. The continuity conditions at the junction points have been presented and analyzed to provide smooth and continuous change of these parameters except for the control variables. The proposed design and construction of trajectory envelopes can be used in the mission design analysis for landing missions. This study also proposes rudimentary solutions for lunar descent and ascent maneuvers in anticipation for sample return missions on the Moon.
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Mechanical engineering, descent, entry, landing, manifolds, precise landing, trajectory envelopes
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58 pages
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