Retropropulsion, or the firing of rocket engines or motors into the direction of flight, is a method of spacecraft deceleration and soft landing that dates back to the early 1960s. Current conceptual designs for landing humans on the surface of Mars require supersonic retropropulsion, or initiation of retropropulsion at supersonic freestream conditions, as part of an extended powered descent phase of flight. The objective of this work is to identify the design parameters and flow condition bounds for self-similar behavior of powered descent aerodynamic interference in relevant flight environments. In applications of sub-scale test data, an “unknown” uncertainty lies in scaling to and from full-scale environments and systems. The issue of scaling for the opposing flows characteristic of powered descent is the focus of the following analysis, using data from wind tunnel testing of figurations with a single, central nozzle as a point of departure.
Scaling and Similitude in Single Nozzle Supersonic Retropropulsion Aerodynamics Interference
AIAA SciTech 2020 ; 2020 ; Orlando, FL, United States
2020-01-06
Aufsatz (Konferenz)
Keine Angabe
Englisch
PARAMETRIC STUDY OF PERIPHERAL NOZZLE CONFIGURATIONS FOR SUPERSONIC RETROPROPULSION
British Library Conference Proceedings | 2010
|