Alternate thermal protection system (TPS) concepts to the Space Shuttle Orbiter were assessed. Metallic, ablator, and carbon-carbon concepts which are the result of some previous design, manufacturing and testing effort were considered. Emphasis was placed on improved TPS durability, which could potentially reduce life cycle costs and improve Orbiter operational characteristics. Integrated concept/orbiter point designs were generated and analyzed on the basis of Shuttle design environments and criteria. A merit function evaluation methodology based on mission impact, life cycle costs, and risk was developed to compare the candidate concepts and to identify the best alternate. Voids and deficiencies in the technology were identified, along with recommended activities to overcome them. Finally, programmatic plans, including ROM costs and schedules, were developed for all activities required to bring the selected alternate system up to operational readiness.
An Assessment of Alternate Thermal Protection Systems for the Space Shuttle Orbiter, Volume 1
1982
66 pages
Report
No indication
English
Manned Spacecraft , Ablative Materials & Ablation , Composite Materials , Ablative materials , Carbon-carbon composites , Heat resistant alloys , Space shuttle orbiters , Thermal protection , Titanium alloys , Cost analysis , Project planning , Spacecraft design , Structural design criteria , Technology assessment , Thermal insulation