Stress analyses of a 3-D braided composite ablative nozzle

Cozart, Aaron; Technologies, United; Shivakumar, Kunigal

doi:10.2514/6.1999-1277

Cited by 5 publications

(3 citation statements)

References 2 publications

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“…The transient thermo-structural response of a composite rocket nozzle employing a thin protective layer was predicted using finite element analysis by Vandenboom and Heister [7], and an assortment of structural and thermal results are presented for both the substrate and the protective layer. Cozart and Hsivakumar [8] performed a finite element axisymmetric stress analysis of a 3-D braided perform ablative composite rocket nozzle, incorporating a material ablation model. In the work of Yoo et al [9], a kick motor nozzle utilizing spatially reinforced composites was subjected to finite element thermo-elastic analysis following the development of a material model used to homogenize various spatial reinforcement architectures.…”

Section: -No Large Deflections In Structurementioning

confidence: 99%

Thermo-Structural Analysis of Combined-Wall Nozzle

Gomaa

Kamal

Al-Sanabawy

2011

International Conference on Aerospace Sciences and Aviation Tec

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In this work, investigation of the thermo-structural response of steel-composite rocket nozzle is carried out using the finite element method; in the form of commercial package ANSYS. A validation of ANSYS for thermal and structural analysis is done first for simple problems, then the analysis done with the nozzle. The result of thermal analysis shows that thermal loads have a great effect in generating a huge amount of stresses on the nozzle structure (more than 60% from the total stresses on the nozzle). The convictive heat transfer coefficient has a great effect on the temperature transferred to the nozzle wall. The composite material resists temperature augmentation, so it is regarded as a thermal protection material.

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Section: -No Large Deflections In Structurementioning

confidence: 99%

Thermo-Structural Analysis of Combined-Wall Nozzle

Gomaa

Kamal

Al-Sanabawy

2011

International Conference on Aerospace Sciences and Aviation Tec

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“…The research shows that the fit clearance of throat insert does not change the overall distribution of stress, but can affect the stress on the matching surface. Cozart and Shivakumar [17] performed a finite element axisymmetric stress analysis of a 3-D braided preform ablative composite rocket nozzle, incorporating a material ablation model. In the work of Yoo et al [18], a kick motor nozzle utilizing spatially reinforced composites was subjected to finite element thermo-elastic analyses following the development of a material model used to homogenize various spatial reinforcement architectures.…”

Section: Introductionmentioning

confidence: 99%

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

Gong¹,

Fan²

2020

International Journal of Aerospace Engineering

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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.

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“…The thermo-structural transient response of a composite rocket nozzle using a thin protective layer was predicted using FEM by Vandenboom and Heister [7], and a variety of structural and thermal results are presented for both the substrate and the protective layer. Cozart and Hsivakumar [8] performed a finite element axisymmetric stress analysis of a 3-D braided perform ablative composite rocket nozzle, including a material ablation study. In the work of Yoo et al [9], a kick motor nozzle made from reinforced composites was subjected to thermo-elastic analysis following the development of a material model used to homogenize various 3-D reinforcement architectures.…”

Section: Introductionmentioning

confidence: 99%

Thermo-structural Analysis of Steel-Composite Wall Nozzle

Gomaa¹,

Huang²

2016

IJMO

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Abstract-Studying of the thermo-structural response of steel-composite rocket nozzle is carried out using ANSYS. A validation of ANSYS for thermal and structural analysis is done first for simple problems, then the analysis done with the nozzle. The result of thermal analysis shows that thermal loads have a great effect in generating a huge amount of stresses on the nozzle structure (more than 60% from the total stresses on the nozzle). The convictive heat transfer coefficient has a great effect on the temperature transferred to the nozzle wall. The composite material resists temperature augmentation, so it is regarded as a thermal protection material.

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Stress analyses of a 3-D braided composite ablative nozzle

Cited by 5 publications

References 2 publications

Thermo-Structural Analysis of Combined-Wall Nozzle

Thermo-Structural Analysis of Combined-Wall Nozzle

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

Thermo-structural Analysis of Steel-Composite Wall Nozzle

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