Studies on Interface Properties of Propellant Liner for Case-Bonded Composite Propellants

Kakade, S. D.; Navale, S. B.; Narsimhan, Vivek

doi:10.1080/713845500

Cited by 19 publications

(18 citation statements)

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“…Later, Yin and Wang [17] reviewed the influence factors, in terms of insulation, liner, propellant, and manufacturing process. Since then, more in-depth investigations still focus on the mechanical and adhesive characteristics of the liner due to the effect of particle size of ammonium perchlorate (AP) [18], additives [19], ingredient migration [20], humidity [21] and curing state of liner [22]. By now, the impact of an individual factor has been investigated comprehensively.…”

Section: Measurement Of Adhesive Propertiesmentioning

confidence: 99%

Review of the Adhesively Bonded Interface in a Solid Rocket Motor

Zhou

Chen

et al. 2015

The Journal of Adhesion

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One of the most challenging requirements in a solid rocket motor (SRM) is the integrity of the charge structure which is a multilayer adhesive joint involving the propellant, liner, and insulation. The propellant/liner/insulation interface is considered to be the weakest part of the whole structure. This interface has some of the usual features of an adhesively bonded interface, as well as its own special characteristics: the co-cured process, ingredient migration between interfaces, and complicated damage mechanisms. We give a technical and critical review of the past fifty years of existing research on many aspects of the propellant/liner/insulation interface in terms of the adhesive properties and adhesive mechanisms, ingredients migration, damage determination, and fracture analysis.To present a comprehensive outline of this interface we also clarify some remaining problems which should be addressed in the future. With significant improvements in the theoretical and experimental studies of the propellant/liner/insulation interface, the problem of integrity failure of the charge structure in SRM will be well resolved. Downloaded by [Cambridge University Library] at 07:15 14 August 2015 2

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Section: Measurement Of Adhesive Propertiesmentioning

confidence: 99%

Review of the Adhesively Bonded Interface in a Solid Rocket Motor

Zhou

Chen

et al. 2015

The Journal of Adhesion

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“…Solid rocket motors are still used today because of its simplicity and reliable launching features . Among the 2 types of basic systems, cartridge‐loaded systems are used for defense applications and the case‐bonded ones for the longer range and higher payload service capacity . Solid rocket motor consists of an outer casing with the purpose to accommodate the propellant grains.…”

Section: Broadness To Srm Insulationmentioning

confidence: 99%

“…This lower density has a prominent significance in the reduced weight of HSM. Therefore, such kind of elastomers can be used for SRM with high payload capacity . In addition to the above mentioned properties, the weight of the launching vehicle and satellite performs a massive role in rocket flight.…”

Section: A Focus On Ehsms For Srmmentioning

confidence: 99%

“…Therefore, such kind of elastomers can be used for SRM with high payload capacity. 22,66,84 In addition to the above mentioned properties, the weight of the launching vehicle and satellite performs a massive role in rocket flight. Table 2 gives the data about the specific gravity of different elastomeric ablators.…”

Section: Epdm-based Hsmsmentioning

confidence: 99%

“…21 Among the 2 types of basic systems, cartridge-loaded systems are used for defense applications and the case-bonded ones for the longer range and higher payload service capacity. 22 Solid rocket motor consists of an outer casing with the purpose to accommodate the propellant grains.Solid rocket motor case is usually fabricated from metals such as steel or carbon/epoxy filament wound composite. 8,10 Figure 1 represents the component parts of an SRM.…”

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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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Propellants

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High Energy Materials

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Studies on Interface Properties of Propellant Liner for Case-Bonded Composite Propellants

Cited by 19 publications

References 1 publication

Review of the Adhesively Bonded Interface in a Solid Rocket Motor

Review of the Adhesively Bonded Interface in a Solid Rocket Motor

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

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