Algorithm Study on Burning Surface Calculation of Solid Rocket Motor with Complicated Grain Based on Level Set Methods

2006 ◽  
Author(s):  
Fei Qin ◽  
He Guoqiang ◽  
Liu Peijin ◽  
Li Jiang
Keyword(s):  
Level Set ◽  
Level Set Methods ◽  
Burning Surface ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Solid Rocket ◽  
Surface Calculation

Efficient Simulation of Grain Burning Surface Regression

2012 ◽  
Vol 466-467 ◽  
pp. 314-318
Author(s):  
You Quan Liu ◽  
Kang Xue Yin ◽  
Fu Ting Bao ◽  
Yang Liu ◽  
En Hua Wu
Keyword(s):  
Performance Evaluation ◽  
Level Set ◽  
Burning Surface ◽  
The Self ◽  
Solid Rocket Motor ◽  
Fast Marching ◽  
Ballistic Performance ◽  
Efficient Simulation ◽  
Effectiveness And Efficiency ◽  
Solid Rocket

The computation of grain burning surface regression plays a very important role in the internal ballistic performance evaluation of solid rocket motor, however, the traditional methods such as geometry-based one could not handle the self-intersection and characteristic geometric element disappearing problems. This paper presents an effective and efficient framework to simulate 3D grain burning surface regression with level set method which is combined with Fast Marching technique to constrain the calculation area only around the burning surface. At last, a typical grain example is given by our framework to verify our method’s effectiveness and efficiency.

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.

NUMERICAL SIMULATION OF INTRA-CHAMBER PROCESSES IN A SOLID ROCKET MOTOR WITH ACCOUNT FOR BURNING SURFACE MOTION

2021 ◽  
pp. 90-105
Author(s):  
A.E. Kiryushkin ◽  
◽  
L.L. Minkov ◽  
Keyword(s):  
Numerical Simulation ◽  
Numerical Algorithm ◽  
Burning Surface ◽  
3D Models ◽  
Stationary Regime ◽  
Rocket Motor ◽  
Chamber Pressure ◽  
Solid Rocket Motor ◽  
Solid Rocket ◽  
Motor Operation

The axisymmetric solid rocket motor (SRM) with an “umbrella” shape is considered in this paper. The numerical algorithm based on the inverse Lax-Wendroff procedure for a gas dynamic equation and on the level-set method for tracking the burning surface is overviewed for internal ballistics problems. Assuming that the propellant combustion proceeds in a quasi-stationary regime and a mass flow from the burning surface depends on the pressure raised to the power of parameter ν, the numerical computations of intra-chamber combustion product flows during the main-firing phase are carried out using the numerical algorithm developed for “umbrella”-shaped SRM at different parameter values. The approximation convergence of flow parameters in a case of the stationary propellant surface and average intra-chamber pressure for all the time of motor operation is examined. The numerical simulation results are obtained and analyzed for different “umbrella” inclination angles. Though the developed algorithm has been applied to the motors with a specific shape, it can also be used for propellant grains of different shapes and is easily extended to 3D models.

scholarly journals Combined Acceleration Methods for Solid Rocket Motor Grain Burnback Simulation Based on the Level Set Method

2018 ◽  
Vol 2018 ◽  
pp. 1-12 ◽  
Author(s):  
Ran Wei ◽  
Futing Bao ◽  
Yang Liu ◽  
Weihua Hui
Keyword(s):  
Level Set Method ◽  
Level Set ◽  
Rocket Motor ◽  
Processing Unit ◽  
Solid Rocket Motor ◽  
Distance Field ◽  
Acceleration Methods ◽  
Generating Method ◽  
Simulation Based ◽  
Solid Rocket

A detailed study of a set of combined acceleration methods is presented with the objective of accelerating the solid rocket motor grain burnback simulation based on the level set method. Relevant methods were improved by making use of unique characteristics of the grains, and graphical processing unit (GPU) parallelization is utilized to perform the computationally intensive operations. The presented flow traced the expansion of burning surfaces, and then Boolean operations were applied on the resulting surfaces to extract various geometric metrics. The initial signed distance field was built by an improved distance field generating method, and a highly optimized GPU kernel was used for estimating the gradient required by the level set method. An innovative Boolean operation method, thousands of times faster than ordinary ones, was ultimately proposed. Performance tests show that the overall speedup was close to 15 on desktop-class hardware, simulation results were proven to converge to analytical results, and the error boundary was 0.25%.

Numerical Simulation of Insulation Layer Ablation in Solid Rocket Motor Based on Fluent

2014 ◽  
Vol 574 ◽  
pp. 224-229
Author(s):  
Jian Li ◽  
Mei Zhang ◽  
Jiang Tao Zhang
Keyword(s):  
Particle Deposition ◽  
Erosion Rate ◽  
Burning Surface ◽  
Rocket Motor ◽  
Insulation Material ◽  
Insulation Layer ◽  
Solid Rocket Motor ◽  
High Erosion Rate ◽  
Discrete Phase ◽  
Solid Rocket

A two-dimensional axisymmetric model was constructed to predict the ablation of the insulation layer in an end burning rocket motor by using the Computational Fluid Dynamics (CFD) software Fluent. The insulation material of graphite was used in the model. The wall surface reactions and discrete phase erosion were applied to simulate the insulation layer ablation. The influence of the burning surface movement was analyzed by using the dynamic mesh method. Numerical results show that the erosion rate increase with the increasing of burning time. The maximum erosion rate occurs at the upstream of the nozzle throat. There has a high erosion rate closing to the burning surface, and it decreases gradually away from the burning surface and becomes zero near the nozzle. It’s found that solid particle deposition appears on the inner surface of combustor closing to the nozzle, and it increases with the increasing of time.

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