High Mass Mars Entry, Descent, and Landing Architecture Assessment

摘要: As the nation sets its sight on returning humans to Moon and going onward Mars, landing high mass payloads ( 2 t) Mars surface becomes a critical technological need. Viking heritage technologies (e.g., 70 sphere-cone aeroshell, SLA-561V thermal protection system, supersonic disk-gap-band parachutes) that have been mainstay of United States’ robotic exploration program do not provide sucient capability land such large payload masses. In this investigation, parametric study entry, descent, design space has conducted. Entry velocity, entry vehicle conguration, mass, approach deceleration were varied. Particular focus is given shape technology trades. Slender bodied vehicles with lift-to-drag ratio (L=D) 0.68 are examined alongside blunt bodies L=D = 0.30. Results demonstrated while increased slender conguration allows for more favorable terminal descent staging conditions, greater structural eciencies body systems along reduced acreage required system aords an inherently lighter vehicle. The trade focuses inatable aerodynamic decelerators (IAD) retropropulsion, as parachute shown be excessively further consideration. While masses (the total at top atmosphere) between 20 100 t considered, maximum 37.3 results. Of particular note, increases, gain in diminishes. It vertical decelerate all considered through atmosphere adequate conditions propulsive descent. A fraction penalty approximately 0.3 exists use vehicles. Another observation investigation aerothermal loads induced from direct trajectory (velocity 6.75 km/s) reduce by 15% compared orbital velocity 4 km/s). should noted both IADs retropropulsion evaluated each masses, congurations, velocities, IAD proved mass-ecient instances. sensitivity these results modeling assumptions was also examined. observed four times sensitive uncertainty than bodies.