Research on thermochemical erosion and thermal protection properties of multiple interface nozzles in long-time working hybrid rocket motors
Author:
Funder
National Natural Science Foundation of China
Publisher
Elsevier BV
Subject
Aerospace Engineering
Reference43 articles.
1. Determining the time-resolved mass flow rates of hybrid rocket fuels using laser absorption spectroscopy;Wang;Acta Astronaut.,2021
2. Numerical simulation of low-melting temperature solid fuel regression in hybrid rocket engines;Rashkovskiy;Acta Astronaut.,2020
3. Numerical analysis of the hybrid rocket motor with axial injection based on oxidizer flow distribution;Tian;Acta Astronaut.,2022
4. Experimental and numerical investigation of swirling H2O2 and polypropylene hybrid rocket motor with regenerative cooling;Li;Acta Astronaut.,2022
5. Experimental investigation of a flow-oriented throttleable injector designed for throttleable hybrid rocket motor;Zhao;Acta Astronaut.,2022
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1. Trajectory/propulsion integrated design optimization of the manned lunar lander propelled by hybrid rocket motors using analytical target cascading;Acta Astronautica;2024-09
2. Hierarchical porous (Ta 0.2Nb 0.2Ti 0.2Zr 0.2Hf 0.2)C high-entropy ceramics prepared by a self-foaming method for thermal insulation;Journal of Advanced Ceramics;2024-07
3. Experimental and numerical investigation on thermochemical erosion and mechanical erosion of carbon-based nozzles in hybrid rocket motors;Aerospace Science and Technology;2024-05
4. Experiments of ablation characteristics for different nozzle materials and transient simulations on thermochemical erosion in hybrid rocket motors;Acta Astronautica;2023-11
5. Numerical Analysis on Nozzle Erosion in Hybrid Rocket Motors with Different Injection Parameters;2023 14th International Conference on Mechanical and Aerospace Engineering (ICMAE);2023-07-18
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