Space Launch System (SLS) Base Convective Environments
Speaker: Manish Mehta, Aerosciences Branch, NASA Marshall Space Flight Center
Presentation
Seminar Slide Deck (PDF-8.4MB)
Abstract
The NASA Space Launch System (SLS) vehicle is composed of four RS-25 liquid oxygen-hydrogen rocket engines in the core-stage and two 5-segment solid rocket boosters at a total lift-off thrust of 8,870,000 lbf and as a result six hot supersonic plumes interact within the aft section of the vehicle during flight. In this presentation, the various trends of the base convective and pressure environments within the core-stage and booster base regions are discussed. In-depth investigation of the base flow physics for nominal and off-nominal flight is presented using shock tunnel instrumentation test data, infrared high-speed imaging, planar laser-induced-fluorescence (PLIF), other new non-intrusive diagnostics and theory. The second component describes the methodology of generating external thermal base design environments from the ground test data and the thermal impacts and design of SLS Block I base components. The third component briefly touches on Green Run Core Stage base heating observations and the associated base aerothermodynamics developmental flight instrumentation (DFI) for the first SLS Block I flight.
Funded by the NASA SLS Program
Biography