Convective Heat Transfer in the Reusable Solid Rocket Motor of the Space Transportation System

Ahmad, Raza

doi:10.1080/01457630500248554

Cited by 10 publications

(3 citation statements)

References 16 publications

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“…According to the findings by Ahmad, the greatest likelihood of nozzle neck ablation is with the greatest heat transfer coefficient, when the materials of the nozzle are the same. 7 There was a maximum temperature of 1434.15 K in the nozzle neck area (Fig. 3).…”

Section: Resultsmentioning

confidence: 98%

Thermo-mechanical analysis of first-stage-adjustment thruster propelled by explosive pressure

Kwon

Lee

et al. 2015

Materials Research Innovations

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A lateral jet thruster operates at high temperature and high pressure, which causes ablation at the nozzle neck and malfunction of the nozzle system. The function of the solid propulsion system's nozzle is to provide thrust to the system by effectively utilising the high temperature gas that is generated in the combustion chamber. The requirements of the lateral propulsion system have to be taken into account in nozzle design, as well as the structural safety of the nozzle itself. An accurate stress analysis therefore needs to be conducted beforehand, simultaneously taking into account the thermal stress caused by the heat transfer between the high temperature gas and the wall, and the mechanical stress resulting from the pressure in the flow path. This study examined nozzle safety according to thruster operating time, where high temperature and high pressure combustion gas explodes to propel the prototype lateral thruster.

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Section: Resultsmentioning

confidence: 98%

Thermo-mechanical analysis of first-stage-adjustment thruster propelled by explosive pressure

Kwon

Lee

et al. 2015

Materials Research Innovations

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“…The heat transfers between the high-temperature gas and the inner wall generally can be classified into convective, radiant and conductive. The forced convective heat is the most significant factor for the heat transfer [23][24][25][26].…”

Section: Introductionmentioning

confidence: 99%

“…radiation and conduction are ignored [23][24][25][26]. The mechanical erosion of the material and the ablation of the inner nozzle wall are also neglected [27,28].…”

Section: Introductionmentioning

confidence: 99%

Probabilistic Reliability Analysis of Carbon/Carbon Composite Nozzle Cones with Uncertain Parameters

Xie¹,

Yang²,

Meng³

et al. 2019

Journal of Spacecraft and Rockets

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Effects of baffle designs on damping acoustic oscillations in a solid rocket motor

Zhao

et al. 2021

Aerospace Science and Technology

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Convective Heat Transfer in the Reusable Solid Rocket Motor of the Space Transportation System

Cited by 10 publications

References 16 publications

Thermo-mechanical analysis of first-stage-adjustment thruster propelled by explosive pressure

Thermo-mechanical analysis of first-stage-adjustment thruster propelled by explosive pressure

Probabilistic Reliability Analysis of Carbon/Carbon Composite Nozzle Cones with Uncertain Parameters

Effects of baffle designs on damping acoustic oscillations in a solid rocket motor

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