The promises of the composite materials with non degradable matrix like carbon or ceramics in rocket propulsion is shown by examples. From an historial point of view, carbon-carbon materials were first used in solid rocket motor nozzles. More recently, successful all composite hot gas valving systems have incorporated not only carbon-carbon materials, but also thermostable insulators and oxidation resistant materials with silicon carbide matrix. These oxidation resistant materials open the way now for liquid propellant rocket applications such as small thrusters and large nozzle exit-cone. The design philosopy to be followed to reach the best compromise between propulsion requirements and material properties is discussed.
High Temperature Composite Materials for Rocket Propulsion
1989
11 pages
Report
No indication
English
Rocket Engines & Motors , Composite Materials , Corrosion & Corrosion Inhibition , Carbon-carbon composites , Heat resistant alloys , Matrix materials , Nozzle design , Rocket nozzles , Silicon carbides , Solid propellant rocket engines , Oxidation resistance , Shear strength , Tensile strength , Thrust chambers , Foreign technology , Design criteria
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