scholarly journals Structural vibrations and internal ballistic modelling of a star-grain solid rocket motor

2021 ◽  
Author(s):  
Sonny Loncaric
Keyword(s):  
Finite Element ◽  
Simulation Model ◽  
Numerical Solutions ◽  
Damping Ratio ◽  
Structural Response ◽  
Rocket Motor ◽  
Numerical Dissipation ◽  
Solid Rocket Motor ◽  
Internal Ballistic ◽  
Solid Rocket

A numerical model is developed to solve the governing equations for the structural dynamics and internal ballistics of a solid rocket motor (SRM). An explicit finite element method is used to solve for the structural response, and an explicit finite volume method is used to solve for the internal ballistic flow. Together, these two numerical solutions are coupled to model the nonsteady behaviour of axial combustion instability in sleeved cylindrical- and star-grain SRMs. The simulation model is used to predict the axial instability in star-grain SRMs. A parametric analysis is made to record the effects of various parameters on the simulation model. These parameters include the numerical dissipation constant, damping ratio and pulsing strength. It is found that both the numerical dissipation constant and damping ratio can, both artificially and physically, affect the finite element structural response of the motor. The pulsing strength affects only the rate at which the do pressure rises as well as how quickly the limiting wave amplitude is reached. A numerical model is developed to solve the governing equations for the structural dynamics and internal ballistics of a solid rocket motor (SRM). An explicit finite element method is used to solve for the structural response, and an explicit finite volume method is used to solve for the internal ballistic flow. Together, these two numerical solutions are coupled to model the nonsteady behaviour of axial combustion instability in sleeved cylindrical- and star-grain SRMs.The simulation model is used to predict the axial instability in star-grain SRMs. A parametric analysis is made to record the effects of various parameters on the simulation model. These parameters include the numerical dissipation constant, damping ratio and pulsing strength. It is found that both the numerical dissipation constant and damping ratio can, both artificially and physically, affect the finite element structural response of the motor. The pulsing strength affects only the rate at which the do pressure rises as well as how quickly the limiting wave amplitude is reached.The detailed analysis of simulated star-grain SRM axial instability reveals the effect of structural vibrations on burning rate augmentation and wave development in nonsteady operation. The variation in oscillation frequencies about a given grain section periphery, and along the grain with different levels of burnback, influences the means by which the local acceleration drives the combustion and flow behavior. The amount of damping also plays a role in influencing the predicted instability symptoms of the motor.

scholarly journals Structural vibrations and internal ballistic modelling of a star-grain solid rocket motor

2021 ◽  
Author(s):  
Sonny Loncaric
Keyword(s):  
Finite Element ◽  
Simulation Model ◽  
Numerical Solutions ◽  
Damping Ratio ◽  
Structural Response ◽  
Rocket Motor ◽  
Numerical Dissipation ◽  
Solid Rocket Motor ◽  
Internal Ballistic ◽  
Solid Rocket

A numerical model is developed to solve the governing equations for the structural dynamics and internal ballistics of a solid rocket motor (SRM). An explicit finite element method is used to solve for the structural response, and an explicit finite volume method is used to solve for the internal ballistic flow. Together, these two numerical solutions are coupled to model the nonsteady behaviour of axial combustion instability in sleeved cylindrical- and star-grain SRMs. The simulation model is used to predict the axial instability in star-grain SRMs. A parametric analysis is made to record the effects of various parameters on the simulation model. These parameters include the numerical dissipation constant, damping ratio and pulsing strength. It is found that both the numerical dissipation constant and damping ratio can, both artificially and physically, affect the finite element structural response of the motor. The pulsing strength affects only the rate at which the do pressure rises as well as how quickly the limiting wave amplitude is reached. A numerical model is developed to solve the governing equations for the structural dynamics and internal ballistics of a solid rocket motor (SRM). An explicit finite element method is used to solve for the structural response, and an explicit finite volume method is used to solve for the internal ballistic flow. Together, these two numerical solutions are coupled to model the nonsteady behaviour of axial combustion instability in sleeved cylindrical- and star-grain SRMs.The simulation model is used to predict the axial instability in star-grain SRMs. A parametric analysis is made to record the effects of various parameters on the simulation model. These parameters include the numerical dissipation constant, damping ratio and pulsing strength. It is found that both the numerical dissipation constant and damping ratio can, both artificially and physically, affect the finite element structural response of the motor. The pulsing strength affects only the rate at which the do pressure rises as well as how quickly the limiting wave amplitude is reached.The detailed analysis of simulated star-grain SRM axial instability reveals the effect of structural vibrations on burning rate augmentation and wave development in nonsteady operation. The variation in oscillation frequencies about a given grain section periphery, and along the grain with different levels of burnback, influences the means by which the local acceleration drives the combustion and flow behavior. The amount of damping also plays a role in influencing the predicted instability symptoms of the motor.

Solid Rocket Motor Finite Element Analysis Based on the Reverse Modeling of ICT Images

2014 ◽  
Vol 599-601 ◽  
pp. 1708-1711
Author(s):  
Peng Li ◽  
Hong Mei Zhou ◽  
Hong Yi Lu ◽  
Min Zhu ◽  
Qing Gui Chen
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Rocket Motor ◽  
Experimental Result ◽  
Solid Rocket Motor ◽  
Element Analysis ◽  
Contour Segmentation ◽  
Modeling Software ◽  
Solid Rocket ◽  
Vector Images

To Evaluate SRM effectively, according to the structure characteristics of solid rocket motor, the series of solid rocket motor ICT images were processed with edge detection ,edge thinning, contour tracing, contour segmentation, and contour fitting. The raster images were converted to vector images which can be recognized by the CAD modeling software. Then, according to the vector images, SRM was modeled by the software, and the model was studied with finite-element analysis. The experimental result indicates that the quality of the model is good, and the result of the finite-element analysis can reflect the state of the experimental SRM.

scholarly journals Thermo-Structural Response Caused by Structure Gap and Gap Design for Solid Rocket Motor Nozzles

Energies ◽  
2016 ◽  
Vol 9 (6) ◽  
pp. 430 ◽  
Author(s):  
Lin Sun ◽  
Futing Bao ◽  
Ning Zhang ◽  
Weihua Hui ◽  
Shaozeng Wang ◽  
...  
Keyword(s):  
Structural Response ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Solid Rocket

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.

A Modified Discriminance in Performance Reliability Simulation of Solid Rocket Motor

2015 ◽  
Vol 798 ◽  
pp. 576-581
Author(s):  
Hao Xu ◽  
Fu Ting Bao ◽  
Chen Cheng ◽  
Bin Hang Wang
Keyword(s):  
Rocket Motor ◽  
Uncertain Parameters ◽  
Sample Analysis ◽  
Solid Rocket Motor ◽  
Ballistic Performance ◽  
Internal Ballistic ◽  
Solid Rocket ◽  
Curve Similarity ◽  
Analysis Of Performance ◽  
Monte Carlo Simulation Model

In the assessment of internal ballistic performance reliability of Solid Rocket Motor (SRM), eigenvalue discriminance method has long been used. In order to avoid the limitations of the traditional methods, a curve similarity discriminance modification combined with Hausdorff Distance was introduced. A Monte-Carlo simulation model of internal ballistic performance was established, and several uncertain parameters were chosen. A sample analysis of performance reliability of a designed SRM was presented. The result was credible, which proved the modification is feasible and it can meet the needs of the assessment of the internal ballistic performance reliability.

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 Numerical Evaluation of the Use of Aluminum Particles for Enhancing Solid Rocket Motor Combustion Stability

2021 ◽  
Author(s):  
David Greatrix
Keyword(s):  
Pressure Wave ◽  
Internal Flow ◽  
Rocket Motor ◽  
Combustion Stability ◽  
Transient Pressure ◽  
Solid Rocket Motor ◽  
Aluminum Particles ◽  
Internal Ballistic ◽  
Reactive Particles ◽  
Solid Rocket

The ability to predict the expected internal behaviour of a given solid-propellant rocket motor under transient conditions is important. Research towards predicting and quantifying undesirable transient axial combustion instability symptoms typically necessitates a comprehensive numerical model for internal ballistic simulation under dynamic flow and combustion conditions. On the mitigation side, one in practice sees the use of inert or reactive particles for the suppression of pressure wave development in the motor chamber flow. With the focus of the present study placed on reactive particles, a numerical internal ballistic model incorporating relevant elements, such as a transient, frequency-dependent combustion response to axial pressure wave activity above the burning propellant surface, is applied to the investigation of using aluminum particles within the central internal flow (particles whose surfaces nominally regress with time, as a function of current particle size, as they move downstream) as a means of suppressing instability-related symptoms in a cylindrical-grain motor. The results of this investigation reveal that the loading percentage and starting size of the aluminum particles have a significant influence on reducing the resulting transient pressure wave magnitude.

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