Numerical Investigation on the Effect of Ammonium Perchlorate Content and Position on the Combustion Characteristics of an Ammonium Perchlorate/Hydroxyl-Terminated Polybutadiene Propellant
Author:
Affiliation:
1. Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory, Northwestern Polytechnical University, Xi’an 710072, China
2. College of Aircraft Engineering, Nanchang Hangkong University, Nanchang 330063, China
Abstract
Funder
Key Laboratory of Science and Technology on Combustion, Internal Flow, and Thermal-Structure Laboratory
Science and Technology Project of Education Department of Jiangxi Province
Jiangxi Province Innovation Leading Talent Project
Publisher
MDPI AG
Subject
Aerospace Engineering
Link
https://www.mdpi.com/2226-4310/10/8/692/pdf
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3. On the combustion of heterogeneous AP/HTPB composite propellants: A review;Dennis;Fuel,2019
4. Yue, S., Liu, L., Liu, H., Jiang, Y., Liu, P., Pang, A., Zhang, G., and Ao, W. (2023). Agglomerate size evolution in solid propellant combustion under high pressure. Aerospace, 10.
5. Aluminium droplets combustion and SRM instabilities;Orlandi;Acta Astronaut.,2019
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