scholarly journals Aluminized composite solid propellant particle path in the combustion chamber of a solid rocket motor

2006 ◽  
Author(s):  
Y. M. Xiao ◽  
R. S. Amano
Keyword(s):  
Combustion Chamber ◽  
Solid Propellant ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Particle Path ◽  
Composite Solid Propellant ◽  
Solid Rocket ◽  
Composite Solid

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 Burning Rate Enhancement Analysis of End-Burning Solid Propellant Grains Based on X-Ray Real-Time Radiography

2020 ◽  
Vol 2020 ◽  
pp. 1-9
Author(s):  
Wei Xianggeng ◽  
Bo Tao ◽  
Wang Pengbo ◽  
Ma Xinjian ◽  
Lou Yongchun ◽  
...  
Keyword(s):  
Burning Rate ◽  
Real Time ◽  
Solid Propellant ◽  
Burning Surface ◽  
Rocket Motor ◽  
Operating Pressure ◽  
Solid Rocket Motor ◽  
X Ray ◽  
The Real ◽  
Solid Rocket

Unexpected pressure rise may occur in the end-burning grain solid rocket motor. It is generally believed that this phenomenon is caused by the nonparallel layer combustion of the burning surface, resulting in the increase of burning rate along the inhibitor. In order to explain the cause of this phenomenon, the experimental investigation on four different end configurations were carried out. Based on the X-ray real-time radiography (RTR) technique, a new method for determining the dynamic burning rate of propellant and obtaining the real-time end-burning profile was developed. From the real-time images of the burning surface, it is found that there was a phenomenon of nonuniform burning surface displacement in the end-burning grain solid rocket motor. Through image processing, the real-time burning rate of grain center line and the real-time cone angle are obtained. Based on the analysis of the real-time burning rate at different positions of the end surface, the end face cone burning process in the motor working process is obtained. The closer to the shell, the higher the burning rate of the propellant. Considering the actual structure of this end-burning grain motor, it is speculated that the main cause of the cone burning of the grain may be due to the heat conduction of the metal wall. By adjusting the initial shape of the grain end surface, the operating pressure of the combustion chamber can be basically unchanged, so as to meet the mission requirements. The results show that the method can measure the burning rate of solid propellant in real time and provide support for the study of nonuniform combustion of solid propellant.

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.

Design of a Solid Propellant Air Turbo Rocket for a Tactical Air-Launched Missile

2007 ◽  
Author(s):  
Fredrik Haglind ◽  
Henrik Edefur ◽  
Stefan Olsson
Keyword(s):  
Solid Propellant ◽  
Combined Cycle ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Gas Generator ◽  
Number Range ◽  
Solid Propellant Rocket ◽  
Solid Rocket ◽  
Novel Concept ◽  
Propellant Rocket

Traditionally, air-launched missiles are powered by a turbojet engine, rocket motor or a ramjet engine. A novel concept that may offer advantages over these concepts is the Air Turbo Rocket (ATR), which is a combined cycle engine, featuring a cycle where the turbine is isolated from the core engine flow entirely and powered by a separate gas generator. This paper is aimed at assessing the suitability of the solid propellant ATR as power source for a tactical air-launched missile. The ATR cycle is designed to achieve optimum performance, and a suitable solid propellant is selected. In addition, a turbojet and a solid rocket motor are designed for the same requirements, and the performances of these three engine concepts are compared. The ATR offers high thrust to weight and thrust to frontal area weight ratios, throttleability, and a wide speed-altitude operating envelope. The calculations suggest that, provided that the afterburning cooling issues can be solved, it would be reasonable to design the ATR such that a stoichiometric fuel/air mixture is obtained in the afterburner. For the Mach number range evaluated here, the ATR may offer advantages over the turbojet and the solid propellant rocket motor.

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