Flow Characteristics with Distance between Solid Propellant Grain and Igniter
نویسندگان
چکیده
منابع مشابه
Acoustic-Mean Flow Interaction in Solid Propellant Rocket Motors
There are several sources for pressure oscillations in solid propellant rocket motors. Oscillatory flow field is one of them. Free shear layers in motor flow field cause vortex shedding. End edges of propellant grains and baffle edge in two-segmented motors are samples of such zones. These vortices move from their forming points and strike the field walls. The kinetic energy of vortices change ...
متن کاملAcoustic-Mean Flow Interaction in Solid Propellant Rocket Motors
There are several sources for pressure oscillations in solid propellant rocket motors. Oscillatory flow field is one of them. Free shear layers in motor flow field cause vortex shedding. End edges of propellant grains and baffle edge in two-segmented motors are samples of such zones. These vortices move from their forming points and strike the field walls. The kinetic energy of vortices change ...
متن کاملDesign and Geometrical Analysis of Propellant Grain Configurations of a Solid Rocket Motor
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 ...
متن کاملacoustic-mean flow interaction in solid propellant rocket motors
there are several sources for pressure oscillations in solid propellant rocket motors. oscillatory flow field is one of them. free shear layers in motor flow field cause vortex shedding. end edges of propellant grains and baffle edge in two-segmented motors are samples of such zones. these vortices move from their forming points and strike the field walls. the kinetic energy of vortices change ...
متن کاملMEMS-based solid propellant micro -rocket with micro-igniter on thin membrane for next generation of low-cost small space and aeronautic engines
A new planar structure of solid propellant micro -rocket for micro-spacecraft and Micro-Air-Vehicle applications is reported in this paper. We have successfully fabricated an array of micro-rockets using MEMS technology. For a lowpower consumption, the micro-igniter used here is a resistor deposited on a low tensile stress thin membrane to ensure a good heat transfer to the propellant. Experime...
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ژورنال
عنوان ژورنال: Journal of the Korean Society of Propulsion Engineers
سال: 2018
ISSN: 1226-6027,2288-4548
DOI: 10.6108/kspe.2018.22.2.096