Radiative Heating Uncertainty for Hyperbolic Earth Entry, Part 2 Comparisons with 1960s-Era Shock-Tube Measurements.
Saved in:
| Title: | Radiative Heating Uncertainty for Hyperbolic Earth Entry, Part 2 Comparisons with 1960s-Era Shock-Tube Measurements. |
|---|---|
| Authors: | Johnston, Christopher O.1,2, Sutton, Kenneth3,4, Prabhu, Dinesh4,5, Bose, Deepak4,6 |
| Source: | Journal of Spacecraft & Rockets. Jan/Feb2013, Vol. 50 Issue 1, p39-47. 9p. |
| Subjects: | Heat radiation & absorption, Atmospheric entry of space vehicles, Martian exploration, Simulation methods & models, Heisenberg uncertainty principle, Uncertainty (Information theory), High temperatures |
| Abstract: | The computational technique and uncertainty analysis presented in Part 1 (Johnston et al., "Assessment of Radiative Heating Uncertainty for Hyperbolic Earth Entry Part 1: Flight Simulation Modeling and Uncertainty," Journal of Spacecraft and Rockets, Vol. 50, No. 1, 2013, pp. 19-38.) for Mars-return radiative heating simulations are applied to 1960s era shock-tube and constricted-arc experimental cases. It is shown that these experiments contain shock-layer temperatures and radiative flux values relevant to the Mars-return cases of present interest. Comparisons between the predictions and measurements, accounting for the uncertainty in both, are made for a range of experiments. A measure of comparison quality is defined, which consists of the percent overlap of the predicted uncertainty bar with the corresponding measurement uncertainty bar. For nearly all cases, this percent overlap is greater than zero, and for most of the higher temperature eases (T > 13, 000 K), it is greater than 50%. These favorable comparisons provide evidence that the baseline computational technique and uncertainty analysis presented in Part 1 are adequate for Mars-return simulations. [ABSTRACT FROM AUTHOR] |
| Copyright of Journal of Spacecraft & Rockets is the property of American Institute of Aeronautics & Astronautics and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
Be the first to leave a comment!
