Dynamic Simulation of Insulation Material Ablation Process in Solid Propellant Rocket Motor

Xu, Yi; Hu, Xu; Yang, Yu Xin; Zeng, Zhuo Xiong; Hu, Chun Bo

doi:10.1061/(asce)as.1943-5525.0000452

Cited by 10 publications

(9 citation statements)

References 27 publications

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“…The "CAD approach" curve, on the other hand, suggests thinner thickness in several regions, implying that the approach failed to accurately predict the erosion. The proposed method satisfies the abovementioned criterion (1).…”

Section: Burnback Modelmentioning

confidence: 83%

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Precise Design of Solid Rocket Motor Heat Insulation Layer Thickness under Nonuniform Dynamic Burning Rate

Wei

Bao

Liu

et al. 2019

International Journal of Aerospace Engineering

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With the purpose of obtaining optimal designs of the heat insulating layers in solid rocket motors, we have proposed a numerical approach to compute the ideal thickness of the heat insulating layer. The proposed method is compatible with solid rocket motors that have any shape and any manner of erosion. The nonuniform dynamic burning rate is taken into consideration to achieve higher accuracy. A high-performance code is developed that uses triangular geometry as an input to allow exchanging data from any CAD platform. An improved geometric intersection algorithm is developed to generate the required sampling points, saving 35% computation time compared to its open source equivalent. Parallel computing technology is utilized to further improve the performance. All operations of the proposed approach can be executed automatically by programs, eliminating the manual work of gathering data from CAD software in the traditional approach. Validation data shows that the proposed approach saves 3.85% of the mass compared to the ordinary design approach. Performance profiling shows that the implemented code operates within 5 seconds, which is much faster than the unoptimized open source version.

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Section: Burnback Modelmentioning

confidence: 83%

“…Previous studies focused on the erosion of HILs were comprehensively summarized by Xu et al [1]. There are simple heat ablation approaches [2,3], thermochemical ablation methods [4,5], and methods which take condensed particles into consideration [6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Precise Design of Solid Rocket Motor Heat Insulation Layer Thickness under Nonuniform Dynamic Burning Rate

Wei

Bao

Liu

et al. 2019

International Journal of Aerospace Engineering

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“…The pre exponential factor, the pressure exponent and the activation energies of the chemical reactions described by Equations (1) and (2) were obtained from [1] and [9] and can be seen in Table 1. The mass consumption rate of CO2 and H2O were calculated as Equations 5 and 6:…”

Section: Thermochemical Ablation Modelmentioning

confidence: 99%

“…Solid rocket motors nozzles operate in severe conditions of pressure and temperature, so that dimensioning the insulation protection is necessary in order to assure its integrity during the operation time [1]. The use of composite and ablative materials for this type of application is consecrated and it has been used since the 1970s in the aerospace industry [2].…”

Section: Introductionmentioning

confidence: 99%

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A Fast Method for Preliminary Evaluation of Chemical Erosion on a Composite Nozzle

Untem¹,

Calciolari²,

Almeida³

et al. 2018

Proceedings of the 4th Brazilian Conference on Composite Materials

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Most solid rocket motors (SRM) make use of polymeric composites as ablative thermal protection system (TPS). One of the main advantages of this type of cooling is its simplicity and cost; however, the mechanism of erosion on the composite surface is very complex and tricky to model. In the present work, an ablation model was developed considering the reaction of H2O and CO2 molecules, present in the combustion gases, with the ablative material. This approach is valuable for a preliminary assessment of the behaviour of ablative layers. The investigation was based on a particular case of a SRM ablative nozzle since it is a critical setup for this type of thermal protection system. The bisection method was used for 02 particular propellant formulations in order to predict the mass consumption rate of the ablative material in function of the nozzle diameter and the mass fraction of aluminium.

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Rocket nozzles: 75 years of research and development

Khare

Saha

2021

Sādhanā

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Dynamic Simulation of Insulation Material Ablation Process in Solid Propellant Rocket Motor

Cited by 10 publications

References 27 publications

Precise Design of Solid Rocket Motor Heat Insulation Layer Thickness under Nonuniform Dynamic Burning Rate

Precise Design of Solid Rocket Motor Heat Insulation Layer Thickness under Nonuniform Dynamic Burning Rate

A Fast Method for Preliminary Evaluation of Chemical Erosion on a Composite Nozzle

Rocket nozzles: 75 years of research and development

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