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Energetic Solid Fuels for Ducted Rockets (II)

✍ Scribed by N. Kubota; Y. Yano; K. Miyata; T. Kuwahara; M. Mitsuno; I. Nakagawa

Book ID
105355733
Publisher
John Wiley and Sons
Year
1991
Tongue
English
Weight
462 KB
Volume
16
Category
Article
ISSN
0721-3115

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✦ Synopsis

Abstract

The combustion characteristics of variable‐flow ducted rockets were evaluated in order to obtain optimum design parameters of the gas generators. The energetic solid fuels used for the gas generators were glycidyl azide polymer (GAP) with burning rate catalysts. The burning rate of GAP based energetic fuels was much higher than that of composite and double‐base based fuel‐rich propellants. The pressure exponent of the burning rate was high enough to obtain a wide range of variable‐flow rat. Two types of combustion test were conducted: a semi‐free jet and a direct connect flow. The pressure‐time response in the primary combustor obtained by the use of a throttable nozzle was evaluated.

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Energetic Solid Fuels for Ducted Rockets
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## Abstract Ducted rockets operate with the combustion of fuel‐rich gas generated in a primary combustor and the ram‐air induced from the atmosphere to a secondary combustor. Thus, the combustion performance depends on the mixing and reaction processes of the fuel‐rich gas and the air flow in the s

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## Abstract Energetic solid fuels composed of modified GAP (glycidyl azide polymer) propellants were formulated in order to obtain optimized combustion characteristics for variable flow ducted rockets. Burning rate in a primary combustor and the combustion efficiency in a secondary combustor were s