A US company has proposed an alternative precursor for the ablative materials used to protect rocket assemblies. In US Patent 6235359 Cordant Technologies Inc suggests using lyocell with a staple length of 100 - 150 mm and average denier of about 5 dpf. Preferably the fibres are untreated before graphitization. It enables spun yarns to be substituted for filament yarns. These yarns may then be woven, plied or wound to provide the desired structure to form a reinforcement for the ablative material. The material is carbonized at 1350 degree C. It is then impregnated with a suitable resin such as a phenolic (SC 1008). In a rocket assembly, the ablative material may be fitted as a multi-layered structure providing an insulation liner, which is cured and fitted as the interior surface of the rockets motor case. Such insulation helps to protect the rocket motor case from the extreme conditions of the burning propellant.
Better ablative material for the protection of rocket assemblies
Ein besserer Ablationswerkstoff für den Schutz von Raketenaggregaten
Advances in Textiles Technology ; Okt ; 4-5
2001
2 Seiten, 1 Bild
Aufsatz (Zeitschrift)
Englisch
Ablation (Luftfahrt) , Raumfahrzeug , Abtragen , Raketenantrieb , carbonfaserverstärkter Kunststoff , Lyocellfaser , Vorläufer (Precursor) , Carbonfaser , Graphitisierung , Spinnfasergarn , Phenolharz , Imprägnieren , Isolierschicht , Schutzschicht , Hitzeschild , Patent , Fertigungsverfahren , Werkstoff
Ablative Material Testing at Lewis Rocket Lab
NTIS | 1997
Ablative Material Testing at Lewis Rocket Lab
NTRS | 1997