Entry, Descent, and Landing technological barriers and crewed MARS vehicle performance analysis

摘要: Abstract Mars has been explored historically only by robotic crafts, but a crewed mission encompasses several new engineering challenges – high ballistic coefficient entry, hypersonic decelerators, guided entry for reaching intended destinations within acceptable margins error in the landing ellipse, and payload mass are all critical factors evaluation. A comprehensive EDL parametric analysis conducted support of architecture evaluating three types vehicles −70° Sphere Cone, Ellipsled SpaceX hybrid called Red Dragon as potential candidate options vehicles. Aerocapture at Martian orbit about 400 km subsequent Entry-from-orbit scenarios were investigated velocities 6.75 km/s 4 km/s respectively. study on aerocapture corridor over range (6–9 km/s) suggests that L/D 0.3 is sufficient aerocapture. Parametric studies varying aeroshell diameters from 10 m to 15 m masses up 150 mt summarized results reveal with 40–80 mt capable delivering cargo order 5–20 mt. For an 20 mt 80 mt, probabilistic Monte Carlo 5000 cases each vehicle run determine final ellipse quantify statistical uncertainties associated trajectory attitude conditions during atmospheric entry. Strategies current technological human rated Entry, Descent, Landing surface presented this study.