COOLING SYSTEM FOR ROCKET MOTOR

PURPOSE:To obtain big cooling effect by substituting ablative shielding material for one part or total of conventional fibrous insulator, and utilizing the heat insulating surface for a heat radiating surface after combustion. CONSTITUTION:In the case of heat radiation of a rocket motor 4, 5 of whic...

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Bibliographische Detailangaben
1. Verfasser:	SHINOZAKI TAKAO
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR WEAPONS
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Beschreibung
Zusammenfassung:	PURPOSE:To obtain big cooling effect by substituting ablative shielding material for one part or total of conventional fibrous insulator, and utilizing the heat insulating surface for a heat radiating surface after combustion. CONSTITUTION:In the case of heat radiation of a rocket motor 4, 5 of which the outer circumferential of a nozzle cone 1 combined with the rocket motor 4, 5 is covered with fibrous insulator 2, at least one part of the fibrous insulator 2 is substituted for ablative shielding material 3. Hereupon, ablation in the ablative shielding material means that heat generated by aerodynamic heating at rocket propulsion is removed from an important part and let a not so important part absorb it. Such related material is selected so as to be material having properties to generate melting, evaporation, and vanishing due to heat absorption.