HYBRID PROPELLANT ROCKET MOTOR
نویسندگان
چکیده
منابع مشابه
Dispersion of Toxic Exhausts from Liquid Rocket Propellant Combustion 25 Dispersion of Toxic Exhausts from Liquid Rocket Propellant Combustion
Environmental impact assessment of liquid rocket motor exhaust obtained due to mainly liquid propellant combustion have been highlighted. Exhaust product analysis has been carried out theoretically by computer software NASA CEC -71 to identify toxic emissions of rocket combustion. In the present study a high volume Air Samplers (APM-430) was deployed at predetermined locations near launch pad f...
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Design and analysis of propellant grain configurations for determination of the grain geometry which is an important and critical step in the design of solid propellant rocket motors, because accurate calculation of grain geometrical properties plays a vital role in performance prediction. The performance prediction of the solid rocket motor can be achieved easily if the burn back steps of the ...
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A comprehensive numerical analysis has been conducted to study the combustion of a double-base homogeneous propellant in a rocket motor. Emphasis was placed on the motor internal flow development and its influence on propellant combustion. The formulation is based on the Favre-averaged, filtered equations for the conservation laws and takes into account finite-rate chemical kinetics and variabl...
متن کاملA Model of Ap/htpb Composite Propellant Combustion in Rocket-motor Environments
A comprehensive theoretical/numerical model for treating AP/HTPB composite-propellant combustion in a rocket-motor environment is presented. The formulation takes into account the conservation equations in both the gas and condensed phases, and accommodates finiterate chemical kinetics and variable thermophysical properties. The processes in the two phases are coupled at the surface to determin...
متن کاملUnsteady Flow Evolution and Combustion Dynamics of Homogeneous Solid Propellant in a Rocket Motor
A time-resolved numerical analysis of combustion dynamics of double-base homogenous solid propellant in a rocket motor is performed by means of a Large-Eddy Simulation (LES) technique. The physiochemical processes occurring in the flame zone and their influence on the unsteady flow evolution in the chamber are investigated in depth. A five-step reduced reaction mechanism is used to obtain the t...
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ژورنال
عنوان ژورنال: International Conference on Aerospace Sciences and Aviation Technology
سال: 1999
ISSN: 2636-364X
DOI: 10.21608/asat.1999.24884