concern regarding the ef%ciency, stability and safety margins of hi-propellant combustion in rocket engines has prompted the investigation of nlany specific aspects of spray evaporation, ignition and combustion previoudy not studied. Thus, early s!,ucties of combustion in liquid rocket engines were based upon the results of the classsid single-component, isolated drop combustion at atmospheric ...

Because of its strong oxidizing properties, high density, low-toxicity and environmentally friendly decomposition products, concentrated hydrogen peroxide has regained popularity as a propellant in many rocket applications. The MEMS-based MIT micro-rocket engine is one such application where 98% liquid hydrogen peroxide and JP7 are proposed as a propellant combination. Like other micro-thruster...

The thrust vector control problem for an upper-stage rocket with propellant slosh dynamics is considered. The control inputs are defined by the gimbal deflection angle of a main engine and a pitchingmoment about the center of mass of the spacecraft. The rocket acceleration due to themain engine thrust is assumed to be large enough so that surface tension forces do not significantly affect the p...

Abstract The 3D flow filling process of LOX (Liquid Oxygen) dome is studied in a liquid oxygen/methane rocket engine. volume, field pressure and velocity distributions oxygen at different time are determined. property propellant the injection characteristic obtained. results show that when has not been filled, state disorder, flows around annular wall middle dome. static near equalizing orifice...