Mehran University Research Journal of Engineering and Technology, 2019 Optimum characteristic length of the combustion chamber of liquid rocket engine is very important to get higher energy from the liquid propellants. Characteristic length is defined by the time required for complete burning of fuel.
Tajwali Khan, Ihtzaz Qamar
doaj
A General Quadrature Solution for Relativistic, Non-relativistic, and Weakly-Relativistic Rocket Equations [PDF]
arXiv, 2015 We show the traditional rocket problem, where the ejecta velocity is assumed constant, can be reduced to an integral quadrature of which the completely non-relativistic equation of Tsiolkovsky, as well as the fully relativistic equation derived by Ackeret, are limiting cases.
arxiv
Current activities at IITRI on high- temperature protective coatings [PDF]
Heat resistant protective coatings for use in liquid propellant rocket ...
Hess, A. L. +2 more
core +1 more source
Analysis of quasi-hybrid solid rocket booster concepts for advanced earth-to-orbit vehicles [PDF]
A study was conducted to assess the feasibility of quasi-hybrid solid rocket boosters for advanced Earth-to-orbit vehicles. Thermochemical calculations were conducted to determine the effect of liquid hydrogen addition, solids composition change plus ...
Andreev T. +7 more
core +2 more sources
On possibility to use flow control units of electromagnetic type for liquid propellant rocket engines [PDF]
, 2001 С. А. Шевченко
openalex +1 more source
Steam balloon concept for lifting rockets to launch altitude [PDF]
arXiv, 2018 Launching orbital and suborbital rockets from a high altitude is beneficial because of e.g. nozzle optimisation and reduced drag. Aeroplanes and gas balloons have been used for the purpose. Here we present a concept where a balloon is filled with pure water vapour on ground so that it rises to the launch altitude.
arxiv
A study of high frequency nonlinear combustion instability in baffled annular liquid propellant rocket motors, volume 1 Final report, 25 Aug. 1969 - 25 Sep. 1970 [PDF]
High frequency nonlinear combustion instability in baffled annular liquid propellant rocket engines - Vol.
Burstein, S. Z., Schechter, H. S.
core +1 more source
Investigation of the existing methods for designing pre-combustion chambers in hybrid rocket engines
Авіаційно-космічна техніка та технологіяHybrid propellant rocket engines (HPRE) have been under development and advancement since the beginning of rocket propulsion research, alongside liquid and solid propellant rocket motors.
Maurício Sá Gontijo
doaj +1 more source
Авіаційно-космічна техніка та технологія, 2017 Interest in storable ecologically friendly propellant has increased recently. One of the reasons for that is convenience in storage, handle and delivery. The most interesting storable propellant for launch vehicles is high-test peroxide with kerosene. A
Михаил Витальевич Андриевский +2 more
doaj +1 more source
Liquid rocket performance computer model with distributed energy release Interim final report, 15 Aug. 1969 - 15 Aug. 1970 [PDF]
Liquid propellant rocket engine performance computer program with distributed energy ...
Campell, D. T. +2 more
core +1 more source