Ignition of a polymer propellant of hybrid rocket motor by a hot particle
Author:
Funder
President of the Russian Federation
Publisher
Elsevier BV
Subject
Aerospace Engineering
Reference20 articles.
1. Thermal characteristics of an N2O catalytic igniter with metal foam for hybrid rocket motors;You;Int. J. Heat. Mass Transf.,2013
2. Additively manufactured acrylonitrile-butadiene-styrene-nitrous-oxide hybrid rocket motor with electrostatic igniter;Whitmore;J. Propul. Power,2015
3. Regression rate behaviors of HTPB-based propellant combinations for hybrid rocket motor;Sun;Acta Astronaut,2016
4. Ranking upper stages in low Earth orbit for active removal;Anselmo;Acta Astronaut,2016
5. Low-frequency feed-system-coupled combustion instability in hybrid rocket motors;Morita;J. Therm. Sci. Technol.,2013
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1. Ignition processes and characteristics of charring conductive polymers with a cavity geometry in precombustion chamber for applications in micro/nano satellite hybrid rocket motors;Defence Technology;2023-05
2. Effect of Fuel Activation Energy on Ignition of Hydrogen Peroxide Hybrid Rocket;Journal of Spacecraft and Rockets;2021-11
3. Combustion characterization of a CH4/O2 rapid mixed swirl torch igniter for hybrid rocket motors;Aerospace Science and Technology;2020-03
4. Numerical simulation of gel fuel gas-phase ignition by a local source of limited heat content;Acta Astronautica;2019-10
5. The gel fuel ignition at local conductive heating;International Journal of Heat and Mass Transfer;2018-12
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