scholarly journals Crack Group Effect Analysis of the Stress-Release Boot of Solid Rocket Motor Based on Numerical Simulation

2021 ◽  
Vol 2021 ◽  
pp. 1-9
Author(s):  
Tianpeng Li ◽  
Junli Han ◽  
Yong He ◽  
Yu Guo
Keyword(s):  
Numerical Simulation ◽  
Low Temperature ◽  
Experimental Test ◽  
Main Crack ◽  
Rocket Motor ◽  
Shielding Effect ◽  
Group Effect ◽  
Solid Rocket Motor ◽  
Stress Release ◽  
Solid Rocket

Due to the complex process of the insulation layer patch in solid rocket motor (SRM), only manual patch could be used. Sometimes weak bonding or debonding in each joint surface was inevitable. This study is aimed at determining the crack group effect of insulation and interfacial debonded crack in the wide-temperature SRM. The crack group appeared in the front area of the ahead stress-release boot and was induced by low temperature, axial overload, or interface bonding failure. Based on the viscoelastic finite element method, singular crack elements and singular interfacial crack elements at the tips of crack group were established to calculate J -integral. Varying according to the length and position of cracks, the J -integral of crack tips was, respectively, calculated to prejudge their stability and the crack group effect. The results showed that collinear crack group appeared in the front stress-release boot layer, and the crack group had a certain shielding effect on the main crack when the SRM was launched at low temperature. When noncollinear crack group appeared in the front stress-release boot layer, the crack group effect changed with the length of the main crack. The crack group first had a shielding effect on the main crack and then had a strong strengthening effect. The experimental test of the simulated specimen revealed that numerical simulation results matched the experimental test results.

Dimension-adaptive algorithm-based PCE for models with many model parameters

2019 ◽  
Vol 37 (2) ◽  
pp. 522-545
Author(s):  
Yangtian Li ◽  
Haibin Li ◽  
Guangmei Wei
Keyword(s):  
Low Temperature ◽  
Adaptive Algorithm ◽  
Rocket Motor ◽  
Uniform Grid ◽  
Model Parameters ◽  
Solid Rocket Motor ◽  
Computational Accuracy ◽  
Content Type ◽  
Invasive Method ◽  
Solid Rocket

Purpose To present the models with many model parameters by polynomial chaos expansion (PCE), and improve the accuracy, this paper aims to present dimension-adaptive algorithm-based PCE technique and verify the feasibility of the proposed method through taking solid rocket motor ignition under low temperature as an example. Design/methodology/approach The main approaches of this work are as follows: presenting a two-step dimension-adaptive algorithm; through computing the PCE coefficients using dimension-adaptive algorithm, improving the accuracy of PCE surrogate model obtained; and applying the proposed method to uncertainty quantification (UQ) of solid rocket motor ignition under low temperature to verify the feasibility of the proposed method. Findings The result indicates that by means of comparing with some conventional non-invasive method, the proposed method is able to raise the computational accuracy significantly on condition of meeting the efficiency requirement. Originality/value This paper proposes an approach in which the optimal non-uniform grid that can avoid the issue of overfitting or underfitting is obtained.

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.

Numerical Simulation of a Dual Pulse Solid Rocket Motor Flow Field

2012 ◽  
Vol 62 (6) ◽  
pp. 369-374 ◽  
Author(s):  
Afroz Javed ◽  
P. Manna ◽  
Debasis Chakraborty
Keyword(s):  
Numerical Simulation ◽  
Flow Field ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Solid Rocket
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