The factors of thermal protection system TPS design for a foldable, flexible aerobrake are discussed and documented in this study, which presents a practical design approach directed at a Centaur upper stage booster. The basics of the navigational guidance and control concerns are briefly described. Pertinent trades between number of aeropasses, TPS material sizing, and propellant weight to meet system mission requirements are presented. The heating environment and its impact on overall design are described. Several thermal and geometric models were constructed to perform preliminary analysis and predict the thermal response of the TPS and selected Centaur components. The TPS simulation subjected the concept TPS to the expected heating environment. The increase in number of aeropasses results in reductions in heating rates, maximum temperatures on aerobrake face, and the maximum dynamic pressure but increases the total integrated heat load. These reductions are translated in design into reduced TPS insulation thickness and weight. The increase in the number of aeropasses also results in an increase in the amount of fuel required to complete the mission. Aerobrake backface temperatures and vortex-induced convection will be the predominant heating source for the protected vehicle during re-entry passes.
Design parameters and environmental considerations for a reusable aeroassisted orbital transfer vehicle
Konstruktionsparameter und Umweltbetrachtungen fuer eine wiederverwendbare luftunterstuetzte Raumfaehre
AIAA-Papers ; Jun ; 1-5
1987
5 Seiten, 5 Bilder, 2 Tabellen, 13 Quellen
Aufsatz (Konferenz)
Englisch
Aeroassisted Orbital Transfer Vehicle Control Technology
NTIS | 1988
|Aeroassisted orbital transfer vehicle control technology
NTRS | 1988
|Aeroassisted orbital transfer mission evaluation
AIAA | 1982
|Guidance trajectories for aeroassisted orbital transfer
NTRS | 1990
|