Lunar/Mars earth return aerocapture heating constraintTrajectory design issues beyond those under consideration in the Aeroassist Flight Experiment (AFE) program and more in line with the Shuttle design concept are presented. This is deemed necessary as flight regimes encountered in Lunar/Mars aerocapture trajectories at Mars and return-to-earth will provide more stringent requirements on vehicle design than AFE and are not exactly quantifiable at this time. Investigations are conducted of areas where explicit trajectory control is practical and can most directly influence constraints critical to vehicle design for manned and unmanned interplanetary missions. Primary consideration is given to the ability to control vehicle heating during entry, and this particular area of Shuttle entry design is discussed in detail.
Document ID
19900065953
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cuthbert, P. A. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Tigges, M. A. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Bryant, L. E. (NASA Johnson Space Center Houston, TX, United States)