@inproceedings{5a9b74a7717c4f96bf7750e7cdcb54c6,
title = "Effect of Secondary Combustion and Flow Mach Number on Base Thermal Environment of Re-Entry Rocket Under Retro-Propulsion",
abstract = "Reusable liquid rockets are crucial for future space transportation. During first-stage re-entry and recovery, the interaction between the retrograde propulsion plume and the free stream is complex, causing severe aerodynamic ablation on the engine nozzle and rocket base. This affects mission success and reusability. This study examines the second-generation 'Raptor' engine's nozzle model, developing single- and triple-nozzle engine models to analyze plume characteristics under varying reverse flow Mach numbers. The impact of secondary combustion on the engine base's thermal environment is also explored using the eddy dissipation model for afterburning reactions. Results show that the peak Mach number in the triple-nozzle wake decreases with increasing flight Mach number, and the rocket base heat flux density is higher on the outer side than the inner side.",
keywords = "Flow characteristics tracking, Rocket recovery, Secondary combustion, Vertical re-entry",
author = "Hao Zheng and Xiangnan Chen and Yong Tang and Baolu Shi",
note = "Publisher Copyright: {\textcopyright} 2025 The Authors.; 8th International Conference on Aeronautical, Aerospace and Mechanical Engineering, AAME 2025 ; Conference date: 28-03-2025 Through 30-03-2025",
year = "2025",
month = nov,
day = "27",
doi = "10.3233/ATDE251388",
language = "English",
series = "Advances in Transdisciplinary Engineering",
publisher = "IOS Press BV",
pages = "78--84",
editor = "Mo, \{John P.T.\}",
booktitle = "Aeronautical, Aerospace and Mechanical Engineering - Proceedings of the 8th International Conference, AAME 2025",
address = "Netherlands",
}