Abstract
The safe dissipation of heat generated in atmospheric braking is a major design concern associated with the re-entry of a space vehicle and is a significant area of research. During re-entry, competing requirements of deceleration, heating, and accuracy of landing or impact must be delicately balanced. In this paper, using simple orbital mechanics and heat transfer equations, a horizontal take-off launcher that is single stage to orbit and designed to take-off and land horizontally was considered to explore how best to minimize the heat generated on the vehicle surface for different re-entry modes.
| Original language | English |
|---|---|
| Pages (from-to) | 33-45 |
| Number of pages | 13 |
| Journal | JP Journal of Heat and Mass Transfer |
| Volume | 10 |
| Issue number | 1 |
| Publication status | Published - Aug 2014 |
| Externally published | Yes |
Keywords
- Heat dissipation
- Re-entry
ASJC Scopus subject areas
- Atomic and Molecular Physics, and Optics