Physics
Scientific paper
Oct 1980
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1980gec..reptqv....&link_type=abstract
Final Report General Electric Co., Philadelphia, PA. Re-Entry Systems Div.
Physics
Atmospheric Entry Simulation, Orbit Transfer Vehicles, Surface Geometry, Thermal Protection, Aerodynamic Configurations, Dynamic Pressure, Impact Loads, Lift, Orbital Velocity, Thermal Protection, Torque
Scientific paper
An atmospheric entry study to fine a generic aerocapture vehicle capable of missions to Mars, Saturn, and Uranus is reported. A single external geometry was developed through atmospheric entry simulations. Aerocapture is a system design concept which uses an aerodynamically controlled atmospheric entry to provide the necessary velocity depletion to capture payloads into planetary orbit. Design concepts are presented which provide the control accuracy required while giving thermal protection for the mission payload. The system design concepts consist of the following elements: (1) an extendable biconic aerodynamic configuration with lift to drag ratio between 1.0 and 2.0; (2) roll control system concepts to control aerodynamic lift and disturbance torques; (3) aeroshell design concepts capable of meeting dynamic pressure loads during aerocapture; and (4) entry thermal protection system design concepts to meet thermodynamic loads during aerocapture.
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