Regression Rate Studies of Aniline Formaldehyde-Red Fuming Nitric Acid Hybrid System
Author:
Affiliation:
1. Birla Institute of Technology, Ranchi, India
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/3.62102
Reference9 articles.
1. TURBULENT BOUNDARY LAYER COMBUSTION IN THE HYBRID ROCKET
2. Regression rates of nonmetalized hybrid fuel systems
3. Pressure dependence of hybrid fuel regression rates.
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1. Solid Amine–Boranes as High-Performance and Hypergolic Hybrid Rocket Fuels;Journal of Propulsion and Power;2016-01
2. Hybrid Rocket Technology;Defence Science Journal;2011-04-27
3. A Preliminary Study of End-Burning Hybrid Rocket. Part 2. Combustion Characteristics.;JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2001
4. A Preliminary Study of End-Burning Hybrid Rocket. Part 1. Combustion Stability.;JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2001
5. Regression rate studies of metalized aniline formaldehyde hybrid fuel;Journal of Spacecraft and Rockets;1976-09
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