Accelerated Aging and Structural Integrity Analysis Approach to Predict the Service Life of Solid Rocket Motor

2015 ◽  
Author(s):  
Dong-mo Zhou ◽  
Xiangyang Liu ◽  
Xin Sui ◽  
Zhi-jun Wei ◽  
Ning-fei Wang
Keyword(s):  
Service Life ◽  
Structural Integrity ◽  
Accelerated Aging ◽  
Rocket Motor ◽  
Analysis Approach ◽  
Solid Rocket Motor ◽  
Solid Rocket ◽  
Integrity Analysis

scholarly journals Analysis of Load Optimization in Solid Rocket Motor Propellant Grain with Pressure Cure

2021 ◽  
Vol 2021 ◽  
pp. 1-11
Author(s):  
Zhanxin Cui ◽  
Haiyang Li ◽  
Zhibin Shen ◽  
Huiru Cui
Keyword(s):  
Attenuation Coefficient ◽  
Structural Integrity ◽  
Great Influence ◽  
Rocket Motor ◽  
Cooling Curve ◽  
Engineering Practice ◽  
Stress And Strain ◽  
Solid Rocket Motor ◽  
Load Optimization ◽  
Solid Rocket

At present, the casting of large-size motors often adopts pressure cure. This technology can effectively reduce the risk of damage to the structural integrity of the grain in the case-bonded casting solid rocket motor. In this paper, ABAQUS is used to establish a finite element model of star-shaped grains. The whole process of pressure cure was simulated and modeled, and the Python script was redeveloped. The Evol evolutionary algorithm was used in ISIGHT to optimize the load parameters such as pressure value, attenuation coefficient of the relief curve, and the attenuation coefficient of the cooling curve. The effects of different pressure values and different cooling and depressurizing rates on the residual stress and strain were analyzed. The optimization results show that the closer the pressure value is to the theoretical pressure, the more significant the effect of pressure cure. However, the effect of stress and strain reduction in different directions is slightly different. The different cooling and pressure relief rates have a great influence on the process quantity. Pressure cure works best when the pressure attenuation coefficient is equal to 6850, and the temperature attenuation coefficient is equal to 8650. The optimization analysis of pressure curing provides a reference for engineering practice.

Analysis on the Structural Reliability of Solid Rocket Motor Grains

2012 ◽  
Vol 503-504 ◽  
pp. 953-957
Author(s):  
Bing Long ◽  
Xin Long Chang ◽  
Bin Jian ◽  
Jian Wei Lai
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Structural Reliability ◽  
Accelerated Aging ◽  
Relaxation Modulus ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
C 50 ◽  
Solid Rocket ◽  
Element Method

Based on Integral Stochastic Finite Element Method (ISFEM), the structural reliability of solid propellant grain was analyzed. Viscoelastic finite element method was determined and ISFEM is utilized to improve calculation efficiency. The thermally accelerated aging experiments at 40°C，50°C，60°C and 70°C were carried out, and the mechanical property parameters were investigated. Considering the randomness of Poisson’s ratio and relaxation modulus, structural reliability and its variation tendency solid rocket motor grain under the ignition pressurization case were investigated in combination with failure criterion. The results show that the reliability of SRM grain descends not evidence before twelve years, but quickly descends after 12 years.

scholarly journals Numerical Simulation of Coupling Thermal and Mechanical Influence on Submerged Nozzle in Solid Rocket Motor

2020 ◽  
Vol 2020 ◽  
pp. 1-9
Author(s):  
Jian-Liang Gong ◽  
Desong Fan
Keyword(s):  
Thermal Loading ◽  
Structural Integrity ◽  
Structural Response ◽  
Mechanical Effect ◽  
Rocket Motor ◽  
Stagnation Temperature ◽  
Solid Rocket Motor ◽  
Aerodynamic Pressure ◽  
Submerged Nozzle ◽  
Solid Rocket

The coupling thermal and mechanical effect on submerged nozzles is important in the design of modern rockets upon thermal loading and aerodynamic pressure. In this paper, a simulation with the subroutine of nonuniform pressure and nonuniform heat transfer coefficient was conducted to study the thermo-structural response of a submerged nozzle at the pressure 6 MPa and stagnation temperature 3200 K. Both the aerodynamic parameters and heat coefficients were obtained through analyzing the flow field. It was found that the thermal loading had an important influence on the stress of throat insert for the solid rocket motor (SRM). The hoop stress increases at first and then decreases with the increase of time for the throat insert. The ground hot firing test of SRM with a submerged nozzle was carried out. The experimental results showed that the structural integrity of the submerged nozzle is very normal during SRM operation. The present method is reasonable, which can be applied to study the thermo-structural response of submerged nozzle for SRM.

scholarly journals Analysis of viscoelastic behavior of a filled elastomer under action of different loads

2017 ◽  
Vol 71 (4) ◽  
pp. 307-317 ◽  
Author(s):  
Nikola Gligorijevic ◽  
Sasa Zivkovic ◽  
Nenad Kovacevic ◽  
Nenad Dimitrijevic ◽  
Bojan Pavkovic ◽  
...  
Keyword(s):  
Tensile Strength ◽  
Service Life ◽  
Structural Integrity ◽  
Probabilistic Approach ◽  
Viscoelastic Body ◽  
Viscoelastic Behavior ◽  
Filled Polymers ◽  
Rocket Propellant ◽  
Solid Rocket ◽  
Integrity Analysis

Mechanical properties of viscoelastic filled polymers strongly depend on temperature and strain rate and vary for several orders of magnitude. During service life, a viscoelastic body, especially carboxy-terminated polybutadiene (CTPB) composite solid rocket propellant grain, is subjected to many stress-inducing loads. Its structural integrity analysis (hereafter: ?structural analysis?), unlike elastic bodies, is quite complex and sometimes impossible under the action of just a single load. An even greater problem occurs when multiple different types of loads act simultaneously. This study is based on a complete uniaxial mechanical characterization of a viscoelastic CTPB composite rocket propellant, made in MTI- -Belgrade, whose results were used for the analysis of the propellant grain reliability. Through an example, this paper shows a behavior of the viscoelastic propellant grain when it is subjected to extremely different environmental loads at the same time. Similar explicit examples are difficult to found in the literature, except in the form of recommended principles for analysis. It is shown that the tensile strength under the action of fast load due to the pressure may be almost 20 times greater than the tensile strength under the slow temperature load. A probabilistic approach is presented in evaluation the reliability and service life. An example is shown for a rocket propellant grain as a viscoelastic body. The presented principles of the analysis can be applied to any arbitrary viscoelastic body in other areas.

scholarly journals Structural integrity analysis and experimental investigation for solid rocket motor grain subjected to low temperature ignition

2019 ◽  
Vol 293 ◽  
pp. 04005
Author(s):  
Zhi-Bin Shen ◽  
Liang Zhang ◽  
Yi-Fei Li
Keyword(s):  
Finite Element ◽  
Low Temperature ◽  
Structural Integrity ◽  
Three Dimensional ◽  
Element Model ◽  
Rocket Motor ◽  
Experimental Result ◽  
Solid Rocket Motor ◽  
Temperature And Pressure ◽  
Solid Rocket

The structural integrity of solid rocket motor(SRM) grain is severely tested owing to the combined action of low temperature and pressure load under the load case of low temperature ignition. The three dimensional finite element model of SRM was created to analyze the structural integrity of the SRM grain subjected to low temperature and ignition pressure based on three dimensional viscoelastic finite element method via MSC.Patran/Marc. Meanwhile, cold pressurization test was applied on certain SRM. The experimental result and numerical result were compared based on uncoupling principal of temperature and pressure. The result show that the safety factor of solid rocket motor grain is 2.46 which can meet the requirement of structural integrity. The experimental results are in good agreement with the simulation results. Relevant research methods and conclusions can provide reference for the design, analysis and test of SRMs.

Effects of Cyclic Loading on Interface of Liner and Propellant

2011 ◽  
Vol 110-116 ◽  
pp. 3512-3517
Author(s):  
Kai Qu ◽  
Xu Dong Zhang ◽  
Jie Zhang
Keyword(s):  
Cyclic Loading ◽  
Service Life ◽  
Stress Amplitude ◽  
Rocket Motor ◽  
Constitutive Behavior ◽  
Solid Rocket Motor ◽  
Cycle Number ◽  
Natural Logarithm ◽  
Damage Law ◽  
Solid Rocket

During the service life of a solid rocket motor, the interface of liner and propellant is subjected to cyclic loading. In order to find the damage law of it, fixed stress amplitude cyclic loading experiment was used. In the process of the experiment, constitutive behavior and dissipative energy mainly researched. The influence of the fixed stress amplitude on properties of liner/propellant was also studied. The results show that the remains strain increased following the increase of cyclic number. The dissipative energy of every cyclic loading is random, so it does not adapt to be damage variable. The stress amplitude and natural logarithm of the cycle number accord with exponent equation.

Review of the Influence of Poisson's Ratio on the Solid Propellant’s Structure and Properties

2014 ◽  
Vol 1030-1032 ◽  
pp. 268-271
Author(s):  
Xiao Zhang ◽  
Jian Zheng ◽  
Wei Peng ◽  
Zhi Xu Gu
Keyword(s):  
Poisson’S Ratio ◽  
Structural Integrity ◽  
Rocket Motor ◽  
Poisson's Ratio ◽  
Research Progress ◽  
Structure And Properties ◽  
Solid Rocket Motor ◽  
Solid Rocket ◽  
The Relationship

In this paper, the influence of Poisson's ratio on the solid propellant’s structure and properties was summarized. Methods and important results were introduced, which indicated the research progress in the relationship between Poisson’s ratio and structural integrity of solid rocket motor (SRM).

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