Analysis of Aeroheating Augmentation due to Reaction Control System Jets on Orion Crew Exploration VehicleThe analysis of effects of the reaction control system jet plumes on aftbody heating of Orion entry capsule is presented. The analysis covered hypersonic continuum part of the entry trajectory. Aerothermal environments at flight conditions were evaluated using Langley Aerothermal Upwind Relaxation Algorithm (LAURA) code and Data Parallel Line Relaxation (DPLR) algorithm code. Results show a marked augmentation of aftbody heating due to roll, yaw and aft pitch thrusters. No significant augmentation is expected due to forward pitch thrusters. Of the conditions surveyed the maximum heat rate on the aftshell is expected when firing a pair of roll thrusters at a maximum deceleration condition.
Document ID
20090024217
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Dyakonov, Artem A. (NASA Langley Research Center Hampton, VA, United States)
Buck, Gregory M. (NASA Langley Research Center Hampton, VA, United States)
Decaro, Anthony D. (Eloret Corp. Sunnyvale, CA, United States)
Date Acquired
August 24, 2013
Publication Date
June 22, 2009
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
LF99-7144
Meeting Information
Meeting: 41st AIAA Thermophysics Conference
Location: San Antonia, TX
Country: United States
Start Date: June 22, 2009
End Date: June 25, 2009
Sponsors: American Inst. of Aeronautics and Astronautics