Combustion performance and scale effect from N2O/HTPB hybrid rocket motor simulations-Reference-Cited by-同舟云学术

Combustion performance and scale effect from N2O/HTPB hybrid rocket motor simulations

Published:2013-04 Issue: Volume:85 Page:1-11
ISSN:0094-5765
Container-title:Acta Astronautica
language:en
Short-container-title:Acta Astronautica

Author:

Shan Fanli,Hou Lingyun,Piao Ying

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference31 articles.

1. Space Propulsion Analysis and Design;Humble,1995

2. D. Eric, J. Dyer, K. Lohner, et al, Nitrous Oxide Hybrid Rocket Motor Fuel Regression Rate Characterization, AIAA Paper 2007-5352, 2007.

3. Experimental investigation of N2O–PMMA lab-scale hybrid rocket motor;Wan;J. Tsinghua Univ. (Sci. Technol.),2007

4. Method for identification the regression rate in hybrid motor;Yang;J. Propul. Technol.,2006

5. C. Carmicino, A.R. Sorge, Performance comparison between two different injector configurations in a hybrid rocket, Proceedings of the EUCASS Conference, Paper 5.01.01, Moscow, Russia, 2005.

Cited by 16 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Experimental regression rate profiles of stepped fuel grains in Hybrid Rocket Engines;Acta Astronautica;2023-03

2. Entropy Generation and Exergy Assessment of Methane–Nitrous Oxide Diffusion Flames in a Triple-Port Burner;International Journal of Energy Research;2023-02-20

3. Restitution methodology for space and time dependent solid-fuel port diameter evolution in hybrid rocket engines;Aerospace Science and Technology;2021-03

4. Role of N2O and equivalence ratio on NOx formation of methane/nitrous oxide premixed flames;Combustion and Flame;2021-01

5. Effect of Diluent Addition on Combustion Characteristics of Methane/Nitrous Oxide Inverse Tri-Coflow Diffusion Flames;Combustion Science and Technology;2020-12-14