Assessment of the Performance of Ablative Insulators Under Realistic Solid Rocket Motor Operating Conditions

Martin, Heath T.

doi:10.1615/intjenergeticmaterialschemprop.2017021828

Cited by 17 publications

(16 citation statements)

References 50 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Input energy warms up the wall (T s ), and the wall temperature approaches the maximum value called ablative temperature (T Abl ). Ablative TPS begins to ablate, and the decomposition of ablative materials is complex, involving many and multifarious physical and chemical processes (Martin 2013). General relation of ablation is presented in Eq.…”

Section: Heat Transfer Disciplinesmentioning

confidence: 99%

A New Approach to Multidisciplinary Design Optimization of Solid Propulsion System Including Heat Transfer and Ablative Cooling

Adami

Mortazavi

Nosratollahi

2017

J.Aerosp. Technol. Manag.

View full text Add to dashboard Cite

AbstrAct:The optimum design of a solid propulsion system consists of optimization of various disciplines including structure, aerothermodynamics, heat transfer, and grain geometry. In this paper, an efficient model of every discipline has been developed, and a suitable framework is introduced for these hard-coupled disciplines. Hybrid optimization algorithm is used to find the global optimum point including genetic algorithm and sequential quadratic programing. To show the performance of the proposed algorithm, the required correction factor values have been carefully derived using comparison between more than 10 real solid propulsion systems and the proposed algorithm results. According to the results, the derived correction factors are close to 1, with scattering level better than 0.97. In addition, it is shown that the proposed algorithm (errors < 8%) is more accurate in comparison with the conventional approach (errors < 17%). Then, for a case study, multidisciplinary analysis has been done based on 3 general objectives including dry mass, total mass, and specific impulse. It means that the optimum specific impulse is not the maximum value and the optimum dry mass is not the minimum value. Finally, the proposed algorithm can be used to directly derive the optimum configuration for every mission requirement.

show abstract

Section: Heat Transfer Disciplinesmentioning

confidence: 99%

A New Approach to Multidisciplinary Design Optimization of Solid Propulsion System Including Heat Transfer and Ablative Cooling

Adami

Mortazavi

Nosratollahi

2017

J.Aerosp. Technol. Manag.

View full text Add to dashboard Cite

show abstract

“…Thermal insulator for rocket motor chamber is one of the most important applications of the elastomeric ablative materials. Combustion of solid rocket motor propellant produces turbulent environment containing gases with a velocity, temperature, and pressure more than 1000 m/s, 3000°C, and 10 MPa, respectively, which destroys any metallic alloy …”

Section: Introductionmentioning

confidence: 99%

“…Some charring ablators, which are made of thermosetting resin, such as phenolics, epoxies, polyesters, or ceramics, become rigid after curing and their surface cracks or blisters when exposed to high temperature and pressures; thus, these materials are essentially unworkable as an insulator for such applications …”

Section: Introductionmentioning

confidence: 99%

“…Combustion of solid rocket motor propellant produces turbulent environment containing gases with a velocity, temperature, and pressure more than 1000 m/s, 3000°C, and 10 MPa, respectively, which destroys any metallic alloy. [1][2][3] Some charring ablators, which are made of thermosetting resin, such as phenolics, epoxies, polyesters, or ceramics, become rigid after curing and their surface cracks or blisters when exposed to high temperature and pressures; thus, these materials are essentially unworkable as an insulator for such applications. 1,2 The flexible polymeric ablatives represent the widest family of sacrificial thermal protection system due to some intrinsic advantages such as tunable density, lower cost, and higher heat shock resistance, good processing, and mechanical properties and good flexibility, which can enable ablative materials to endure a variety of stresses due to operation and temperature changes.…”

Section: Introductionmentioning

confidence: 99%

“…[1][2][3] Some charring ablators, which are made of thermosetting resin, such as phenolics, epoxies, polyesters, or ceramics, become rigid after curing and their surface cracks or blisters when exposed to high temperature and pressures; thus, these materials are essentially unworkable as an insulator for such applications. 1,2 The flexible polymeric ablatives represent the widest family of sacrificial thermal protection system due to some intrinsic advantages such as tunable density, lower cost, and higher heat shock resistance, good processing, and mechanical properties and good flexibility, which can enable ablative materials to endure a variety of stresses due to operation and temperature changes. [3][4][5][6] Recent advances in nanocomposite materials have been especially realized in their heat resistance and ablative performance due to their improved thermo-physical and mechanical properties, which are important to enhance the insulation performance especially for rocket motor chamber in aerospace applications.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Ablation behavior of organoclay‐NBR insulator: Modeling and experimental

2018

View full text Add to dashboard Cite

Summary Nitrile‐based nanocomposite heat insulators are very attractive materials compared with their similar nonelastomeric counterparts, due to their higher deformation bearing capacity in special applications. Modeling of these ablative nanocomposites enables us to determine the exact required thickness of the insulator and temperature distribution across it at predetermined thermal conditions. The complete form of the ablation equation is a transient nonlinear second‐order differential equation with variable temperature‐dependent thermo‐physical properties, which must be determined during thermal degradation. In this work, in addition to experimental investigation of ablative elastomeric nanocomposites based on NBR, the ablation process is modeled analytically with perturbation theory in the Lagrangian coordinate system because of surface recession and moving boundaries. Kirchhoff transformation was used to get rid of the temperature dependence of k in each zonal of virgin and char. The theoretical results were confirmed by experimental data obtained from the oxyacetylene flame test. The results proposed a competitive nitrile‐based nanocomposite heat insulator with superior ablation properties: mass ablation rate 0.014 g s−1, linear ablation rate 0.012 mm s−1, and insulating index number 6800 s m−1, under a standard test with a heat flux of 2500 kW m−2 for 15 seconds.

show abstract

Acrylonitrile butadiene rubber‐based heat shielding materials for solid rocket motors: Impact of metal–organic frameworks on thermal and mechanical properties

Elashker,

Zorainy,

Zaghloul

et al. 2024

Polymers for Advanced Techs

View full text Add to dashboard Cite

The thermal protection system (TPS) plays a major role in shielding solid rocket motors (SRMs) against structural failure from excessive heating. This study was directed at the recent innovation in flame‐retardant materials used for thermal insulation, with a particular focus on integrating metal–organic frameworks (MOFs) to bolster thermal stability. Three targeted transition metal‐BDC MOFs (MIL‐88(Fe), MOF‐71(Co), and MOF‐5(Zn)) were hydrothermally synthesized and the effect of incorporating these MOFs into nitrile butadiene rubber (NBR) composites was tracked. In general, the addition of the MOFs improved the interfacial compatibility and the processing of the composites. Additionally, experimental investigations have shown that all MOFs improved the mechanical properties of the NBR composite materials. Specifically, the addition of MOF‐5 has been found to increase the maximum tensile strength to 13 MPa, while MIL‐88 increased the elongation at break to 67.1%. In order to evaluate the thermal stability and ablative resistance of the prepared composites, the oxy‐acetylene flame test was utilized. Results showed that the efficiency of the composite as thermal insulation is highly dependent on the MOF type and the metal included. The impact of MOF‐71(Co) on thermal insulation displayed the least linear and mass ablation rates (0.0168 mm/s and 0.057 g/s, respectively) along with the lowest recorded back‐face temperatures, owing to the formation of a thick and compact char layer upon exposure to flames.

show abstract

Assessment of the Performance of Ablative Insulators Under Realistic Solid Rocket Motor Operating Conditions

Cited by 17 publications

References 50 publications

A New Approach to Multidisciplinary Design Optimization of Solid Propulsion System Including Heat Transfer and Ablative Cooling

A New Approach to Multidisciplinary Design Optimization of Solid Propulsion System Including Heat Transfer and Ablative Cooling

Ablation behavior of organoclay‐NBR insulator: Modeling and experimental

Acrylonitrile butadiene rubber‐based heat shielding materials for solid rocket motors: Impact of metal–organic frameworks on thermal and mechanical properties

Contact Info

Product

Resources

About