Доступ предоставлен для: Guest
Портал Begell Электронная Бибилиотека e-Книги Журналы Справочники и Сборники статей Коллекции
International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN Печать: 2150-766X
ISSN Онлайн: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v5.i1-6.1080
pages 1059-1071

ZERO-DIMENSIONAL UNSTEADY INTERNAL BALLISTIC MODELING

A. Annovazzi
Fiat Avio - Comprensorio BPD, Colleferro, Rm, Italy
A. Tamburini
Department of Chemical, Production, Computing and Mechanical Engineering, University of Palermo, Viale delle Scienze bdg. 6, 90128 Palermo, Italy
Fabio Gori
Department of Mechanical Engineering, University of Rome "Tor Vergata", Via del Politecnico 1, 00133 Rome, Italy

Краткое описание

Design of solid rocket motors requires theoretical models for prediction/test analysis having particular characteristics of effectiveness and short computation time, especially when these models are used for statistical calculations as scattering analysis or thrust imbalance evaluation between two coupled flight boosters. To this purpose, a specific internal ballistic model was developed and it is under validation at Fiat Avio-BPD with the following requirements: 1) the flow field solution in the propellant grain channel is obtained considering mass adduction, port area change, erosive burning, and different burn rate for each motor segment; 2) the motor ignition transient is described under unsteady conditions in the simplest way taking into account igniter mass flow rate, flame spreading, and chamber filling. These two requirements were properly combined through: 1) a steady-state solution of the propellant grain flow channel with a convenient linear combination of simple one dimensional flow in integral form (thus allowing Mach number, pressure, propellant mass flow rate, burn rate, etc. along the motor axis to be calculated); 2) unsteady internal ballistic model based on zero-dimensional operating conditions. Pressure, temperature, burn rate, and chamber volume are integrated in time taking into account the effective pressure and burn rate values obtained from the previous point 1 by means on iterative process. A good match was obtained during ignition transient and steady-state phase comparing the obtained results with more sophisticated models, and also with experimental measurements.


Articles with similar content:

NUMERICAL MODEL FOR DOUBLE BASE SOLID PROPELLANT COMBUSTION
International Heat Transfer Conference 9, Vol.4, 1990, issue
Jean-Michel Most, Farhoud Faddoul , Michel Champion
A NUMERICAL SIMULATION OF A PULSE DETONATION ENGINE WITH HYDROGEN FUELS
International Journal of Energetic Materials and Chemical Propulsion, Vol.5, 2002, issue 1-6
Houshang B. Ebrahimi, Charles L. Merkle
EFFECT OF AMBIENT PRESSURE, OVERALL INPUT EQUIVALENCE RATIO AND RESIDENCE TIME ON CARBON PARTICULATE FORMATION AND OXIDATION IN A CONFINED SPRAY FLAME
Journal of Flow Visualization and Image Processing, Vol.14, 2007, issue 1
R. J. Crookes, A. Demosthenous
CFD ANALYSES OFLOW FREQUENCYCOMBUSTION INSTABILITYIN SOLID PROPELLANT ROCKET MOTORS
International Journal of Energetic Materials and Chemical Propulsion, Vol.6, 2007, issue 4
M. Hanzawa, Takakazu Morita, Toru Shimada
EXPERIMENTAL STUDY OF MICROTHRUSTER HEAT LOSS
International Journal of Energetic Materials and Chemical Propulsion, Vol.8, 2009, issue 4
Alexander. B. Kiskin, Vladimir Zarko, Oleg G. Glotov, Vladimir N. Simonenko, Lev K. Gusachenko