Short Notice only given as follows: Because of their well known specific strength, stiffness and excellent durability properties, advanced composites are being considered for primary structures in launch vehicles, crew modules and various components for increased performance and cost reduction. Therefore, it is prudent and beneficial to review the engineering practices and lessons learned in connection with their use in related aeronautic and energy applications, where they are already replacing formerly used metallic materials. Examples of composite components will be shown for the reusable space shuttle orbiter where a number of different composite systems performed very satisfactorily. In addition, very large potential polymer composite designs for future launch vehicles will be discussed. Among them are payload shrouds, interstage structures and the typical intertank shell, wherein thrust booster rockets are often attached between the core stage propellant and oxidizer tanks. In addition, cryogenic propellant composite vessels of different sizes and shapes were fabricated with mostly excellent results, although some spectacular failures were also observed. High pressure composite overwrapped vessels, with and without metallic liners, will be described. Compared to widely used metallic materials, some special features of composites are listed. Relevant design allowables, depending on mission requirements, will be summarized and currently used design practice for aircraft and spacecraft in the US will be reviewed. The well-known “building - block” approach, which is often used to design military as well as civilian aircraft, will be summarized. Some of the most popular micromechanics and macromechanics computer programs used to analyze composite structures, especially with finite elements, will be listed. Although very high temperature composites like carbon/carbon, carbon/ceramic and ceramic/ceramic fiber/matrix systems are also selectively used, the focus in our discussion will be on advanced polymer matrix, carbon/glass fiber systems.
Potential Composite Structures for NASA Future Launch Vehicles and Crew Spacecraft
2011
1 Seite
Conference paper
English
Komposit , Kostenreduktion , Verbundstruktur , primäres Gefüge , Raumfähre , Polymermatrix-Verbundwerkstoff , Rakete , Verbundbauteil , Standmenge , Energieeinsatz , metallischer Werkstoff , Treibstoff , Oxidationsmittel , Verbundwerkzeug , Hochdruck (Mechanik) , Kohlenstoff , Luftfahrzeug , keramische Faser , Glasfaser
Potential Composite Structures for NASA Future Launch Vehicles and Crew Spacecraft
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