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 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.

scholarly journals Roll Amplification of Solid Rocket Motor in LAPAN Sounding Rocket

2020 ◽  
Vol 18 (1) ◽  
Author(s):  
Oka Sudiana
Keyword(s):  
Combustion Chamber ◽  
Flight Test ◽  
Rocket Motor ◽  
Sounding Rocket ◽  
Exhaust Gas ◽  
Solid Rocket Motor ◽  
Sounding Rockets ◽  
Roll Rate ◽  
Satellite Launch Vehicle ◽  
Solid Rocket

Sounding rockets have been used for scientific research and implemented in meteorological and upper atmosphere studies since the late 1950s. Sounding rockets are sub-orbital carriers that follow a parabolic trajectory from launch to landing. Supporting the roadmap of Satellite Launch Vehicle development, LAPAN had launch The Sounding Rocket Program. A sensitive amplification from the production of an unpredicted roll rate was detected during the boost of the sounding rocket, despite of the tail wings in cruciform configuration at last flight test. One of this phenomenon can be influenced by the flow field of the combustion chamber during boosting time. The basic idea of this research is to model the roll amplification effect as a swirling motion of portion of exhaust gas that participate to the rotation dynamics of the rocket rather than to exit immediately flow the combustion chamber. Available flight data where is obtained from last flight test presented. It is shown the presence of a significant roll amplification when solid rocket motor is used during burning time. The result has a good agreement to presence of a portion of exhaust gas influence an unpredicted roll amplification.

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