Thermal Cyclic Stress Analysis of a Solid Rocket Motor

Tunç, Birkan; Özüpek, Şebnem; Podnos, Evgeny; Arkun, Ugur

doi:10.2514/1.a34237

Cited by 15 publications

(6 citation statements)

References 15 publications

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“…They studied the structural deformation law of the charge under the conditions of solidification cooling and working internal pressure. Birkan et al [5] and colleagues analysed the threedimensional stresses of a rocket engine under a cyclic temperature load. The propellant composition model considers the effects of viscoelasticity, deformation, temperature, pressure, and softening under monotonous and cyclic loading.…”

Section: Introductionmentioning

confidence: 99%

Structural response analysis of a solid rocket motor charge under temperature and internal pressure loads

Liu,

2024

J. Phys.: Conf. Ser.

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To study the structural integrity of a solid rocket motor under low temperature load, internal pressure load, and two combined loads, based on the linear viscoelastic model, the structural response of a solid rocket motor under low temperature load, internal pressure load and two combined loads were analyzed by ANSYS finite element software, and the temperature field and strain field of charge loading were obtained. The Von Mises strain distribution of the solid rocket motor along the axial characteristic line is obtained. The results are: Under the combined action of low temperature load, internal pressure load, and two kinds of loads, the maximum Von Mises strain appears at the transition position between the blade joint and the barrel section, which is the most dangerous position for charging.

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Section: Introductionmentioning

confidence: 99%

Structural response analysis of a solid rocket motor charge under temperature and internal pressure loads

Liu,

2024

J. Phys.: Conf. Ser.

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“…Solid rocket motors (SRMs) have been developed as the preferred method of powering most missiles and rockets for military, commercial and space applications [1]. The solid propellant grains are one of the important components of SRMs, and their mechanical behavior has a significant influence on the normal operation [2][3][4]. It is essential to understand the behaviors of solid propellants under different conditions.…”

Section: Introductionmentioning

confidence: 99%

Experimental study on self-heating phenomena of CMDB/HTPB propellant under intermediate strain rate compression load

Wang

Zhang

et al. 2023

J. Phys.: Conf. Ser.

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Self-heating behaviour of solid propellants under intermediate strain rate compressive loading have been studied. Effects of two intermediate strain rate (1 s-1 and 150 s-1) of the CMDB/HTPB propellants were investigated. The compression test was conducted using a hydraulic testing machine and the self-heating temperatures were measured by an infrared camera. The results show the following: (1) For CMDB propellant, the surface temperature of specimens rapidly increased at the initial period, then decreased due to the movement of the high temperature region caused by deformation, and then increased again. Finally, the surface temperature slowly decreased due to heat transfer to the surroundings. Infrared thermography showed the formation of a hot spot. Cracks were initiated and gradually expanded to the interior area during compression. (2) For HTPB propellant, the surface temperature of specimens increased slightly. Compared with CMDB specimens, there was no significant damage to HTPB specimens. (3) For both CMDB and HTPB propellants, the temperature distribution of specimens was non-homogeneous. At the centre of the specimen surface, the temperature is the highest. The self-heating temperatures of propellant increased with increasing the strain rate. However, the difference is slight for HTPB propellant, whereas it is considerable for CMDB propellant.

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“…Yılmaz et al [13] present a response surface Methodology for the assessment of the service life of solid rocket motors under random storage and transportation loads and form limitstate functions to predict failure. Tunç et al [14] performed a novelty analysis which lies in the use of a propellant constitutive model to analyse solid rocket motor under cyclic temperature loading. Milos [15] performed a specific methodology which make a transition from one point of stress concentration to two points to minimized the stress and strain values of a star-type solid propellant by varying the sectional geometric parameters of the grain without compromising its performance.…”

Section: Introductionmentioning

confidence: 99%

Rapid optimization method of solid rocket motor propellant with structural strength

Guo,

Xu,

Chen

et al. 2023

Propellants Explo Pyrotec

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To design a solid rocket motor with a high mass ratio, it is necessary to find out the parameters of the grain shape to meet the structural strength under volume loading fraction and initial burning areas conditions. A rapid optimization method for complex grain of solid rocket motors based on parametric modelling and GA‐BP is proposed. Through the sensitivity analysis of the geometric parameters related to the grain, the sensitive parameters are determined. 30 groups of parameters are determined by the mixed horizontal orthogonal test and the learning samples of the neural network are obtained by FEA. The artificial neural network is established based on the FEA results, and the accuracy of the network is verified by 10 groups of test data sampled by the LHS method. The comparison results show that the prediction error of the maximum Von Mises strain is 5.09 %, the prediction error of the volume loading fraction is 0.16 %, and the prediction error of the initial burning surface is 0.865 %. Based on this, the neural network prediction results are optimized as a function of fitness in GA, and the optimization results show that the maximum strain is reduced by 20.41 % while the constraints are satisfied.

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Thermal Cyclic Stress Analysis of a Solid Rocket Motor

Cited by 15 publications

References 15 publications

Structural response analysis of a solid rocket motor charge under temperature and internal pressure loads

Structural response analysis of a solid rocket motor charge under temperature and internal pressure loads

Experimental study on self-heating phenomena of CMDB/HTPB propellant under intermediate strain rate compression load

Rapid optimization method of solid rocket motor propellant with structural strength

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