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Numerical Simulation Of Two-Phase Flow Field In Spinning Solid Rocket Motor

Posted on:2006-06-07Degree:MasterType:Thesis
Country:ChinaCandidate:C H SunFull Text:PDF
GTID:2132360155468567Subject:Aerospace Propulsion Theory and Engineering
Abstract/Summary:PDF Full Text Request
On the engineering application, the method of rotating stabilization is usually used to guarantee the directional stability in flight of rocket system because of its validity and simpleness. Rotating acceleration has inevitable influence on the work process of Solid Rocket Motor: flow of combustion chamber and nozzle is changed; the pressure, mass flow rate and the specific impulse of Solid Rocket Motor are affected by the spinning. Failure of internal insulator protection is caused by the serious situation of spinning and makes metals and metals oxide slag accumulation increased on the propellant surface and hull of motor. Therefore, the discussion of these problems on the spinning-induced effect on solid rocket motor has an important and practical significance. Two-phase flow field of spinning solid rocket motor is simulated, and gas-particle of two-phase is analyzed in this paper.The Mini-type experimental motor is used as research object in this paper. The basic theories of the solid rocket motor, the method of grid generation, discrete equations and coupled two-phase flow flied are introduced in detail. Firstly, based on the above, when two-phase flow is not taken into account, RNGk - ε model is used to calculate pure gas flow flied of solid rocket motor, and parameters are obtained in the flow field. Varieties of parameters agreed with the results of former literature. Based on calculation of pure gas, gas flow field is compared that of different rotating speed (25n/s, 60n/s and 100n/s) .Secondly, Euler-Lagrange model is used to solve the two-phase flow of solid rocket motor, and the behavior and varieties of parameters of differentdiametric particles (1μm , 5μm and 10 μm ) are studied in internal flow flied.Lastly, two-phase flow flied is studied under spinning (60n/s and 100n/s) condition, integral calculation of the two-phase flow is completed in the spinning SRM combustion chamber and nozzle, and the behavior and varieties of parameters of different diametric particles are studied in spinning internal flow flied thoroughly. The analysis of result and discussion are presented by comparison to two-phase flow flied of no-spinning case. This paper lays a solid foundation to study internal ballistics problem of spinning solid rocket motor in the future.
Keywords/Search Tags:swirling solid rocket motor, combustion chamber and nozzle, two-phase flow, numerical simulation, KNGk-ε model, Euler-Lagrange model
PDF Full Text Request
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