scholarly journals Analytical Prediction for Grain Burn Time and Burning Area Kinematics in a Solid Rocket Combustion Chamber

Ballistics ◽  
2019 ◽  
Author(s):  
Charles A. Osheku ◽  
Oluleke O. Babayomi ◽  
Oluwaseyi T. Olawole
Keyword(s):  
Combustion Chamber ◽  
Analytical Prediction ◽  
Solid Rocket

Solid Rocket Motor Combustion Chamber Aeroacoustics

AIAA Journal ◽  
1978 ◽  
Vol 16 (11) ◽  
pp. 1123-1124
Author(s):  
Warren C. Strahle ◽  
John C. Handley
Keyword(s):  
Combustion Chamber ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Solid Rocket

Particle Tracking in Combustion Chamber of Solid Rocket Motor

2001 ◽  
Author(s):  
Yumin Xiao ◽  
R. S. Amano ◽  
Timin Cai ◽  
Jiang Li ◽  
Guoqiang He
Keyword(s):  
Boundary Conditions ◽  
Combustion Chamber ◽  
High Speed ◽  
Rocket Motor ◽  
Surface Velocity ◽  
Surface Boundary ◽  
Solid Rocket Motor ◽  
Two Phase ◽  
Solid Rocket ◽  
Propellant Surface

Abstract It has been a challenge to investigate how to trace particles in a solid rocket motor (SRM) using aluminized composite solid propellant and submerged nozzle. In using CFD simulations, the boundary conditions for the ejecting particles constrain their trajectories, hence these affect the two-phase flow calculations, and thus significantly affect the evaluation of the slag accumulation. The RTR (X-ray Real-time Radiography) technique is a new method to detect the particles in a firing SRM. A method was developed to simulate the particle ejection from the propellant surface. The moving trajectories of metal particles in a firing combustion chamber were measured by using the RTR high-speed motion analyzer. Numerical simulations with different propellant-surface boundary conditions were performed to calculate particle trajectories. Through this study an appropriate surface velocity condition on the propellant surface was discovered. The method developed here can be used for the future CRM research.

scholarly journals Increase in Performance of Laser Ignition Micro Solid Rocket by Control of Combustion Chamber Pressure

2013 ◽  
Vol 61 (1) ◽  
pp. 9-15 ◽  
Author(s):  
Yusuke MASUDA ◽  
Hiroyuki KOIZUMI ◽  
Tomoyuki HAYASHI ◽  
Masakatsu NAKANO ◽  
Kimiya KOMURASAKI ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Chamber Pressure ◽  
Laser Ignition ◽  
Solid Rocket

New Method to Determine the Velocities of Particles on a Solid Propellant Surface in a Solid Rocket Motor

2005 ◽  
Vol 127 (9) ◽  
pp. 1057-1061 ◽  
Author(s):  
Yumin Xiao ◽  
R. S. Amano ◽  
Timin Cai ◽  
Jiang Li
Keyword(s):  
Boundary Conditions ◽  
Combustion Chamber ◽  
Solid Propellant ◽  
Two Phase Flow ◽  
New Method ◽  
Phase Flow ◽  
Solid Rocket Motor ◽  
Two Phase ◽  
Solid Rocket ◽  
Propellant Surface

Use of aluminized composite solid propellants and submerged nozzles are common in solid rocket motors (SRM). Due to the generation of slag, which injects into a combusted gas flow, a two-phase flow pattern is one of the main flow characteristics that need to be investigated in SRM. Validation of two-phase flow modeling in a solid rocket motor combustion chamber is the focus of this research. The particles’ boundary conditions constrain their trajectories, which affect both the two-phase flow calculations, and the evaluation of the slag accumulation. A harsh operation environment in the SRM with high temperatures and high pressure makes the measurement of the internal flow field quite difficult. The open literature includes only a few sets of experimental data that can be used to validate theoretical analyses and numerical calculations for the two-phase flow in a SRM. Therefore, mathematical models that calculate the trajectories of particles may reach different conclusions mainly because of the boundary conditions. A new method to determine the particle velocities on the solid propellant surface is developed in this study, which is based on the x-ray real-time radiography (RTR) technique, and is coupled with the two-phase flow numerical simulation. Other methods imitate the particle ejection from the propellant surface. The RTR high-speed motion analyzer measures the trajectory of the metal particles in a combustion chamber. An image processing software was developed for tracing a slug particle path with the RTR images in the combustion chamber, by which the trajectories of particles were successfully obtained.

scholarly journals Numerical Study on Response Characteristics of Solid Rocket Pintle Motor

2019 ◽  
Author(s):  
Jeevan Sapkota ◽  
Yi Hua Xu ◽  
Hai Jun Sun
Keyword(s):  
Flow Field ◽  
Combustion Chamber ◽  
Total Pressure ◽  
Numerical Study ◽  
Rocket Motor ◽  
Chamber Pressure ◽  
Head Model ◽  
Solid Rocket Motor ◽  
Rapid Changes ◽  
Solid Rocket

Pintle technology is currently a versatile technology used in a solid rocket motor (SRM) to control the desired thrust by changing the nozzle throat area, while effectively controlling the chamber pressure at the same time. The sudden movement of the pintle can induce rapid changes in the flow field and the occurrence of pressure oscillations inside the combustion chamber. The analysis of such rapid changes is essential to design an efficient controllable pintle rocket motor for a better thrust regulation. Two-dimensional axisymmetric models with mesh generation and required boundary condition were designed to analyze the effects of three different pintle head shape models in SRM thrust regulation effect. Dynamic mesh method was used with specific velocity for moving plug/pintle in the numerical analysis of SRM thrust regulation. The effects of different pintle head models on the flow field, combustion chamber pressure, mass-flow rate, thrust and Mach number were investigated. According to the analysis of total pressure response time, the simulation data revealed that circular pintle head model responded faster among three different models. According to the thrust effect, parabolic pintle has the maximum value of thrust and the greatest total pressure recovery coefficient among all pintle head models.

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