Parametric Study on Solid Rocket Motor Ignition Transient and Pressure Oscillations Onset
Author:
Affiliation:
1. Department of Mechanical and Aerospace Engineering, University of Rome “La Sapienza,” 00184 Rome, Italy
2. ESA, 2200 AG Noordwijk, The Netherlands
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.B35494
Reference31 articles.
1. Starting Transient of Solid-Propellant ocket Motors with High Internal Gas Velocities
2. Radiation effects on 1-D ignition transient analysis of SRM
3. Prediction of ignition transients in solid rocket motors employing canted pyrogen igniters
4. 3D turbulent Navier Stokes simulations of ignition transients in solid rocket motors
5. Numerical Simulation of Axisymmetric Solid Rocket Motor Ignition Transient with Radiation Effect
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2. Numerical Simulation of Ignition Transient for Solid Rocket Motors with Large Aspect Ratio;2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE);2021-07-16
3. Study on maximum pressure rise with igniter mass in tubular grain rocket motor;SCI TECHNOL ENERG MA;2021
4. A Model for Igniter Mass Flow Rate History Evaluation for Solid Rocket Motors;International Journal of Aerospace Engineering;2019-12-31
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