Properties of Agglomerate-Reduced Propellant Under Solid Rocket Motor Conditions

To improve understanding of the combustion properties of agglomerate-reduced propellants under solid rocket motor conditions and to compare their combustion properties between combustor conditions and rocket motor conditions, agglomerate-reduced propellants have been subjected to a series of contras...

Full description

Saved in:
Bibliographic Details
Published in:Journal of propulsion and power 2019-03, Vol.35 (2), p.352-358
Main Authors: Zhou, Xu-yuan, Huang, Feng-lei, Yang, Rong-jie, Li, Jian-min, Li, Shi-peng, Li, Ziyan, Zhang, Wei-hai, Jiang, En-zhou, Zhang, Yong-li
Format: Article
Language:English
Subjects:
Ablative materials
Agglomeration
Aluminum
Combustion chambers
Combustion efficiency
Insulation
Particle size
Propellants
Properties (attributes)
Rocket engines
Rockets
Solid propellant rocket engines
Thrust chambers
Citations: Items that this one cites
Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:To improve understanding of the combustion properties of agglomerate-reduced propellants under solid rocket motor conditions and to compare their combustion properties between combustor conditions and rocket motor conditions, agglomerate-reduced propellants have been subjected to a series of contrastive experiments. The burning agglomerate particle size, ablation, composition of combustion residue, and combustion efficiency have been studied under solid rocket motor conditions and compared with data obtained under high-pressure combustor conditions. The results indicate that, both in the high-pressure combustor and in the solid rocket chamber, the agglomerate-reduced propellant efficiently reduced the burning agglomerate particle size and the ablation of the insulation material, and it promoted a higher combustion efficiency of aluminum as compared to common propellants.
ISSN:0748-4658
1533-3876
DOI:10.2514/1.B37209