Aerodynamic requirements for a Mars rover/sample return aerocapture vehicleThe sensitivity of Martian aerocapture performance to L/D and flight path angle is studied. By adding the minimum energy constraint to the classical corridor width definition, an L/D of at least 0.8 was found to be necessary to ensure a 3.0-deg actual corridor width. The plane change desired during the aeropass was also found to affect L/D requirements.
Document ID
19890038127
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ess, Robert H., Jr. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Munday, Stephen R. (NASA Johnson Space Center Houston, TX, United States)