The Regression Rate-Based Preliminary Engineering Design of Hybrid Rocket Combustion System
نویسندگان
چکیده
The paper presents a useful engineering model for the design of preliminary hybrid rocket engines. This involves experimentally obtained equation regarding speed burning interface between solid fuel and gaseous phase, called regression rate. rate characterizes mass additionally oxidizer through imposed ratio these rates during combustion. is applied to combustion using pure HTPB oxygen was developed three cases, constant rate, flow O/F (ratio fuel). evaluates initial port geometry, oxygen, time, thrust at sea level, time-dependent functions rates, thrust. It assumed that formula applies any time These evaluations can also be other fuel/oxygen couples by knowing correct
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ژورنال
عنوان ژورنال: Processes
سال: 2022
ISSN: ['2227-9717']
DOI: https://doi.org/10.3390/pr10040775