Thermal and ablative properties of silicone insulation

Yamada, Susumu; Serizawa, C.; Kato, Kazushige

doi:10.2514/6.1997-3259

Cited by 8 publications

(8 citation statements)

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“…DC 93‐104, another prominent silicon insulator, is composed of silicone elastomer loaded with silica, silicon carbide, and carbon fibers . It has high viscosity, high char retention, and low ablation rate even under the domination of high shear stress environments that has been used as protective coating for rocket motor cases and ramjet combustion chambers . DC 93‐104 was modified with asbestos or PI fibers .…”

Section: A Focus On Ehsms For Srmmentioning

confidence: 99%

“…144,145 It has high viscosity, high char retention, and low ablation rate even under the domination of high shear stress environments 20 that has been used as protective coating for rocket motor cases 120 and ramjet combustion chambers. 99,146,147 DC 93-104 was modified with asbestos or PI fibers. 148 Stephens et al 149 insulator for ramjet combustor.…”

Section: Silicon Rubber-based Hsmsmentioning

confidence: 99%

“…Generally, insulation used in SRM is composed of organic rubber such as an aramid fiber–filled EPDM . Ethylene propylene diene monomer rubber is a terpolymer of ethylene, propylene, and a diene component (M includes the rubbers having a saturated main chain of methylene group).…”

Section: A Focus On Ehsms For Srmmentioning

confidence: 99%

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Recent developments in elastomeric heat shielding materials for solid rocket motor casing application for future perspective

George

Panda

Mohanty

et al. 2017

Polymers for Advanced Techs

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Catastrophic breakdown that occurs during the flight of supersonic vehicles demands more focused research in the insulation of rocket engines. At present, optimization of polymeric ablatives as viable insulation for solid rocket motor casing has a prominent role in the successful mission of rockets. Among polymers, elastomer serves an imperative part. Comprehensive investigations were disclosed, especially in the elastomeric heat shielding materials with various reinforcing agents. In this paper, research progress of mostly used elastomers is reviewed, and a circumstantial understanding about the features of ablation and insulation has been validated. 2-4 Therefore, to protect the vehicle from miserable failure of spacecraft, some design features are added to cope with the aerodynamic heating. 5Thermal protection system (TPS) materials impart heat shield to protect the structure, aerodynamic surface and the payload of missiles, and those vehicles interacting with the hypersonic environment. 6,7 Polymeric ablative materials serve to effect as TPS that defends space vehicles and probes during the atmospheric entry; they are effective to produce passively cooled rocket combustion chambers 8 and to render insulation to the solid rocket motors (SRMs) at high temperature. [9][10][11] Although some nonpolymeric materials such as inorganic polymers/ceramics or metals have been used as ablative TPS, polymeric ablatives represent the most flexible category of ablatives. In contrast to the inorganic polymers, polymer ablatives have more inborn benefits: high-heat shock resistance, lower density, good mechanical strength, and thermal insulation capabilities. 12The broad range of heat shielding materials (HSMs) for rocket motor casing is produced from reinforced thermosets or elastomers. [13][14][15][16][17][18][19] The most assuring material for the HSM for rocket motors is the elastomers, which can be produced as rubbers, foamed rubbers, or fiber-reinforced composite materials. On the grounds of lightweight, low thermal conductivity, stability in the mechanical and thermal stresses during the operation, elastomeric HSMs (EHSMs) can find relevance in the insulation of SRM casing where thermal insulation is a prime necessity. They do not possess the ability to form cokes without the introduction of special additives due to the linear chain structure of elastomers, thus no solid carbonic residue on thermal decomposition.Also, elastomers have high elongation at break and the capacity to withstand the mechanical and the thermal stresses during the manufacturing and in use. 20This review puts the elastomeric materials as ablative insulators for SRM into frame and would confer the readers the progress that has been attained in developing relatively low surface eroding and ablative insulating systems for SRM. These systems can be used to manufacture variety of ablative TPS systems for rocket motor casing application and would provide an idea regarding the composite system that would behave elastomeric as well as ablative. Scrutini...

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Section: A Focus On Ehsms For Srmmentioning

confidence: 99%

Section: Silicon Rubber-based Hsmsmentioning

confidence: 99%

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Recent developments in elastomeric heat shielding materials for solid rocket motor casing application for future perspective

George

Panda

Mohanty

et al. 2017

Polymers for Advanced Techs

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“…Baldwin from the US Navy Joint Institute developed a highethylene-component silicone rubber insulation coating, and the test results showed that the ablative performance of the new silicone rubber insulation coating was better than the general room temperature-vulcanized (RTV) silicone rubber [1]. The CELERG company put forward a variety of thermal insulation layer design schemes, and the feasibility of the schemes was verified by experiments [2]. Zhang et al explored the impact factors of silicone rubber ablation performance according to formulas using different raw materials [3].…”

Section: Introductionmentioning

confidence: 99%

Effects of Oxygen Content on the Ablation Behavior of Silicone Rubber-Based Insulation Material

Shi

Zha

et al. 2019

International Journal of Aerospace Engineering

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A self-designed oxygen-kerosene ablation system was employed to research the ablation properties of silicone rubber-based insulation material under different oxygen-rich conditions, that is, 0%, 5.00%, 7.71%, 17.01%, and 18.50%. The morphology of posttest specimens was analyzed via a scanning electron microscope (SEM), and the ablation rates were calculated. Experimental results showed that when the particle concentration was a fixed value, the mass and the linear ablation rates increased first and then decreased with the rise of oxygen content; the maximum values were 0.572 g/s and 0.933 mm/s, respectively. Under high oxygen-rich conditions, the formation of silicone rubber restricted the further increase of the ablation rates, filling more gaps of the reaction layer with liquid silicone rubber. Meanwhile, the thickness of the liquid glass layer attached to the surface was increased, which acted as a buffer against the impacts and erosion of particles and retarded the consumption and recession of materials. Excess oxygen spread to the edge of the ablation pit and reacted. Finally, these led to the increase in diameter of the ablation pit and the decrease of two types of ablation rates.

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“…PAMs are also used to manufacture passively cooled rocket combustion chambers and to provide thermal protection to propulsion devices such as solid rocket motors (SRMs) . Such a wide range of heat shields is generally produced using reinforced thermosets or elastomers: a wide literature survey on the different types of PAMs was provided by Natali et al To date, TPSs are typically designed as rigid aeroshell systems (RASs), i.e., as a rigid monolithic heat shields (Figure a). However, the technology of RASs is rapidly approaching its limit: in fact, even considering the larger launchers, the payload fairing of the rocket (the payload fairing of a rocket is the nose cone, the volume of the vehicle which hosts the satellite or the probe) strongly limits the diameter of the TPS.…”

Section: Introductionmentioning

confidence: 99%

An Armadillo-Like Flexible Thermal Protection System for Inflatable Decelerators: A Novel Paradigm

Natali

Rallini

Puglia

et al. 2013

Macromol. Mater. Eng.

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Polymeric ablative materials play a strategic role in the whole aerospace industry: they are used to produce the thermal protection system (TPS), which protects vehicles during the hypersonic flight through a planetary atmosphere. To date, TPSs are typically designed as rigid monolithic heat shields. Inflatable deployable aeroshells (IDAs) offer an alternative to rigid TPSs: IDAs are based on the use of flexible TPSs (FTPSs). State of the art FTPSs can handle heat fluxes up to approximately 20 W cm−2. However, next generation FTPSs for IADs should be able to survive heat fluxes up to 150 W cm−2. To satisfy these stringent requirements, we propose a radically brand‐new paradigm of flexible TPS based on the use of state of the art elastomeric ablatives (EPDM/Aramid) employed to produce the insulation liners for solid rocket motors. This class of ablatives is able to survive heat fluxes in the range of (300–1000) W cm−2. Most important, we envisioned to introduce an “Armadillo‐Like” design in which a series of overlapping sacrificial movable tiles could work as a continuous flexible thermal barrier.

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Thermal and ablative properties of silicone insulation

Cited by 8 publications

References 0 publications

Recent developments in elastomeric heat shielding materials for solid rocket motor casing application for future perspective

Recent developments in elastomeric heat shielding materials for solid rocket motor casing application for future perspective

Effects of Oxygen Content on the Ablation Behavior of Silicone Rubber-Based Insulation Material

An Armadillo-Like Flexible Thermal Protection System for Inflatable Decelerators: A Novel Paradigm

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