ノズル試験のための端面燃焼固体ロケット・モータの開発(<特集>観測ロケット基礎開発研究特集号)

概要

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An end-burning solid motor has been developed, using hard-type polyvinyl chloride restrictor. This polyvinyl chloride tube capable of being expanded remarkably in the radial direction by the internal stress relaxation due to heating, was proved to be feasible as a restrictor for end-burning motors. The motors were applied for testing rocket nozzle insert materials: graphites, metal-oxide coating graphites, tungsten coating graphite, silicon-carbide coating graphite, sintered copper-tungsten, silicon nitride and miscellaneous fiber-reinforced plastics. Five propellants with widely different flame temperatures, contents of condensed combustion products, oxidation characteristics and firing durations were used. The material performing best with these propellant except in the case of oxygen-augmented motor was some graphites on which tungsten was deposited with the reduction of WFe- Simple graphite, refractory metal oxide and silicon carbide coating graphites, sintered copper-tungsten and silicon nitride indicated poor resistance to erosion or thermal cracking at severer conditions. Though fiber reinforced plastic nozzle inserts were the least erosion-resistant materials, they are promising for the application to giant rocket motors in view of good resistance to thermal stress, isotropic erosion rates and production feasibility.
宇宙航空研究開発機構の論文