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Analysis of aeroheating augmentation due to reaction control system jets on orion crew exploration vehicle
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Decaro, Anthony D. Buck, Gregory M. Dyakonov, Artem A. |
| Copyright Year | 2009 |
| Description | The 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. |
| File Size | 2502817 |
| Page Count | 13 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20090024217 |
| Archival Resource Key | ark:/13960/t5z65hf39 |
| Language | English |
| Publisher Date | 2009-06-22 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Hypersonics Flight Conditions Aerodynamic Heating Afterbodies Continuums Roll Crew Exploration Vehicle Plumes Aerothermodynamics Yaw Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
