Selection of Materials and Design of Multilayer Lightweight Passive Thermal Protection System

Kumar, Sachin; Mahulikar, Shripad P.

doi:10.1115/1.4031737

Cited by 45 publications

(8 citation statements)

References 23 publications

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“…From the thermal point of view, a material should have low thermal conductivity and high specific heat. For finding the best candidate materials and their combinations (elastomer plus mineral fillers and/or fibers), several models and theoretical developments are continuously under way [23,24].…”

Section: Polymeric Insulators For Solid Propellant Rocket Motorsmentioning

confidence: 99%

Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review

et al. 2020

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This review addresses a comparison, based on the literature, among nitrile rubber (NBR), ethylene-propylene-diene-monomer rubber (EPDM), and polyurethane (PU) elastomeric heat shielding materials (EHSM). Currently, these are utilized for the insulation of rocket engines to prevent catastrophic breakdown if combustion gases from propellant reaches the motor case. The objective of this review is to evaluate the performance of PU–EHSM, NBR–EHSM, and EPDM–EHSM as insulators, the latter being the current state of the art in solid rocket motor (SRM) internal insulation. From our review, PU–EHSM emerged as an alternative to EPDM–EHSM because of their easier processability and compatibility with composite propellant. With the appropriate reinforcement and concentration in the rubber, they could replace EPDM in certain applications such as rocket motors filled with composite propellant. A critical assessment and future trends are included. Rubber composites novelties as EHSM employs specialty fillers, such as carbon nanotubes, graphene, polyhedral oligosilsesquioxane (POSS), nanofibers, nanoparticles, and high-performance engineering polymers such as polyetherimide and polyphosphazenes.

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Section: Polymeric Insulators For Solid Propellant Rocket Motorsmentioning

confidence: 99%

Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review

et al. 2020

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“…It is extensively being used in accelerator physics experiments like LHC [11]. Moreover, it has also been applied in high temperature programs in order to protect the sensitive devices from damages due to extreme temperatures like transatmospheric space vehicles [3], hypersonic vehicles to reduce the aero- dynamic heating [12], etc. Cryogenic propellant and high temperature fuel are also using MLI technique for storage purpose [1].…”

Section: Introductionmentioning

confidence: 99%

Improvement in the performance of multilayer insulation technique and impact in the rare physics search experiments

Singh,

Chaubey

et al. 2021

Preprint

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Providing thermal insulation to systems at very low temperature from surroundings, involves blocking the transport of thermal energy−regular or enhanced, taking place through radiative, conductive and convective processes. For instance, the enhancement of radiative heat transport that takes place by infra−red or far infra−red light at low temperature is due to diffractive propagation. The wavelength of light in this part of the spectrum usually lie in the range of mm to cms. Hence it can get bent across an obstacle while propagating forward. Apart from radiative, the convective and conductive processes also get affected due to appearance of non−linearities in the modes of lattice vibrations and anomalies in material transport due to the appearance of vorticity and turbulence in the intervening media. The Multilayer insulation (MLI) technique has offered a robust thermal protective mechanism to provide proper insulation to the cold walls of the cryostats from the heat of the surroundings (basically the radiation heat load). This work is focussed on the estimation of performance and efficiency of the MLI technique as well as exploration of its versatile applicability. Three different spacer materials such as Dacron, Glass−tissue, and Silk−net with radiation shields are selected for the intervening medium in the present study. This article explores the thermal performance of MLI system by changing the physical parameters (emissivity and residual gas pressure), varying the geometry of the radiation shields (perforation styles of radiation shields) and by analyzing the effect of arrangement of radiation shields on the conduction heat load. The predictions of analytical models−Modified Lockheed equation, Lockheed Martin Flat Plate equation and McIntosh's approach are compared for the performance of MLI systems and for the applicable choice in future experiments. This analysis is concluded by studying the possibility of using MLI technique in the health sector by reducing the evaporation rate of liquid Oxygen (LO 2 ) during pandemic situations e.g., in COVID−19.

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“…The A-TPS needs to be lightweight and barrier of the aerodynamic heating loads for the space application. The RL serves as direct jet impingement resistant purpose and requires high ablation resistance, high decomposition temperature, and moderate thermal conductivity [2]. The IL maintains the interior temperature of the space vehicle and is typically low density and low thermal conductivity [1][2].…”

Section: Introductionmentioning

confidence: 99%

Additive Manufacturing of Multi-Functional Lattice Structured-Based Concepts for Thermal Protection System

Yee,

Wu,

Langston

et al. 2020

SAMPE 2020 | Virtual Series

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The potential of lattice structure as a dual-layer meta-material for ablative thermal protection system (A-TPS) was investigated. The geometry of the dual-layer sample comprises a solid Polyether-ketone-ketone (PEKK) recession layer (RL) and a lattice-structure insulating layer (IL). The lattice structure was printed by Fused Filament Fabrication (FFF) process and designed with three different topologies (3D honeycomb, Gyroid, and Schwarz D) with different relative densities (50% and 70%). The dual-layer lattice structures were tested in Oxy-Acetylene Test Bed (OTB) with 100 W/cm 2 heat flux for 30 seconds. The temperatures at the end of RL and IL were compared and the feasibility of using lattice structure as light weight heat insulation material was validated. The results can integrate with impact absorption properties of lattice structure and optimize the performance of TPS for various mission requirements.

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Selection of Materials and Design of Multilayer Lightweight Passive Thermal Protection System

Cited by 45 publications

References 23 publications

Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review

Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review

Improvement in the performance of multilayer insulation technique and impact in the rare physics search experiments

Additive Manufacturing of Multi-Functional Lattice Structured-Based Concepts for Thermal Protection System

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