TABLE OF CONTENTS In this chapter, several single components in mechanical systems are taken for analysis, requirements are indicated, and how the optimum material is chosen in each case is discussed. Much of the justification given for optimum material selection is qualitative, although in a few specific cases MPE analysis and MPI calculations are included.
When the space vehicle is sent into orbit or returns from orbit, an enormous amount of heat is generated. This heat needs to be either dissipated into space or prevented from entering into the interior of the vehicle. The material on the skin of the orbiter should have high melting or fusion temperature. In addition to enormous compressive and shearing forces, the outer skin experiences extreme acoustic noise of high intensity (165 decibels at launch) in some areas. The thermal insulation on the skin of the orbiter must be able to withstand not only the high temperatures, but also the high degree of thermal expansions and subsequent thermal stresses developed. The material should possess high strength and resist both tensile and shear stresses; it should also have excellent resistance to cracking and flaking. Ceramics are the chosen materials for thermal insulation applications. Special processing with selected ceramics is applied to fulfill the requirements.
The orbiter s outer skin is covered with different ceramic materials, depending on the temperatures seen. Let us look at the underside of the fuselage and wings that are protected with over 23,000 high temperature reusable surface insulation tiles (HRSIT) developed...
