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Feasibility Study of SSTO Base Heating Simulation in Pulsed-Type FacilitiesA laboratory simulation of the base heating environment of the proposed reusable Single-Stage-To-Orbit vehicle during its ascent flight was proposed. The rocket engine produces CO2 and H2, which are the main combustible components of the exhaust effluent. The burning of these species, known as afterburning, enhances the base region gas temperature as well as the base heating. To determine the heat flux on the SSTO vehicle, current simulation focuses on the thermochemistry of the afterburning, thermophysical properties of the base region gas, and ensuing radiation from the gas. By extrapolating from the Saturn flight data, the Damkohler number for the afterburning of SSTO vehicle is estimated to be of the order of 10. The limitations on the material strengths limit the laboratory simulation of the flight Damkohler number as well as other flow parameters. A plan is presented in impulse facilities using miniature rocket engines which generate the simulated rocket plume by electric ally-heating a H2/CO2 mixture.
Document ID
Document Type
Conference Paper
Park, Chung Sik (NASA Ames Research Center Moffett Field, CA United States)
Sharma, Surendra (NASA Ames Research Center Moffett Field, CA United States)
Edwards, Thomas A.
Date Acquired
August 20, 2013
Publication Date
January 1, 1995
Subject Category
Launch Vehicles and Launch Operations
Meeting Information
20th International Symposium on Shock Waves(Pasadena, CA)
Funding Number(s)
PROJECT: RTOP 242-10-01
Distribution Limits
Work of the US Gov. Public Use Permitted.