<i>Rocket Propulsion Elements</i>

Sutton, George P.; Seifert, Howard S.

doi:10.1063/1.3066790

Cited by 827 publications

(928 citation statements)

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“…Substances such as iron oxide increase the burning rate, lithium fluoride decreases the burning rate and powdered charcoal helps to keep the combustion steady [4]. These materials help to tailor the burning rate to fit the grain design and thrust-time requirements.…”

Section: Additivesmentioning

confidence: 99%

“…The fuels and oxidizers taken separately are generally un-reactive. The propellants are used in a number of engines such as space lunches, missile and gun [16]. Different chemical ingredients and their proportions result in different physical and chemical properties, combustion characteristics, and performance.…”

Section: Propellant Ingredientsmentioning

confidence: 99%

“…These propellants are well known for good performance characteristics. Nevertheless, their limitations and liabilities regarding toxicity, operational handling and environmental impact are also well documented [4].…”

Section: Introductionmentioning

confidence: 99%

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Optimal design of a composite propellant formulation using response surface methodology

Hamed¹,

Ogunleye

Osheku³

2017

Advances in Materials Science

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There is a continuous demand for high performance composite propellant formulations to meet mission requirements. The performance of composite propellant formulations can be enhanced by optimizing propellant formulation. However, the main objective of this study is to formulate a composition for composite propellant by optimizing the specific impulse which is the measure of propellant performance. A central composite design (ccd) consisting five ingredients (ammonium nitrate, powdered aluminum, polyester resin, ammonium dichromate and powdered charcoal) at five levels was used to formulate optimum propellant formulation from composite materials of ammonium nitrate based propellant verified for propellant characteristics using propellant performance evaluation programme (propep 3). The responses evaluated are specific impulse, characteristic velocity, density, temperature and molecular weight. Response surface methodology was used to analyze the results of the ccd of the composite formulations. The optimum values for specific impulse, characteristic velocity, density, temperature and molecular weight of the mixture from the surface plot are 212.178 s, 1335.81 m/s, 1640.6 k g/m3, 1968.73 k and 21.7722 g/mol respectively. The optimum predicted specific impulse was 212.178 s at composite composition of 73.61% ammonium nitrate, 4.36% powdered aluminum, 14.39% polyester resin, 5.10% ammonium dichromate and 2.54% powdered charcoal. The propellant optimum composition validated with propep 3 are in good agreement with each other in their accompany propellant characteristics. Therefore, the optimal propellant formulation enhanced the performance of solid propellants.

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Section: Additivesmentioning

confidence: 99%

Section: Propellant Ingredientsmentioning

confidence: 99%

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Optimal design of a composite propellant formulation using response surface methodology

Hamed¹,

Ogunleye

Osheku³

2017

Advances in Materials Science

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“…This is probably caused by the polymeric matrix, which is responsible for the mechanical properties of the propellant, that is already formed and has the usual trend of hardening by loss of plasticizer and oxidation [2,[14][15] .…”

Section: Sem Analysesmentioning

confidence: 99%

“…The composite propellant based on the hydroxyl-terminated polybutadiene binder usually contains about 80 weight percent ammonium perchlorate (AP) and aluminum powder (Al) solids, 15 weight percent hydroxyl-terminated polybutadiene (HTPB) and five weight percent additives, of which the plasticizer represents up to 60 weight percent [1][2][3] .…”

Section: Introductionmentioning

confidence: 99%

Diffusion of plasticizer in a solid propellant based on hydroxyl-terminated polybutadiene

et al. 2010

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Abstract:The aim of this work was to determine the dioctyl azelate (DOZ) plasticizer diffusion coefficient (D) for samples containing the interfaces of rubber, liner and solid composite propellant based on hydroxyl-terminated polybutadiene (HTPB). The samples used in the diffusion study were aged up to 31 days after the cure period at 80 °C. A computer program implementing a mathematical model of Fick's second Law of diffusion was developed to calculate the diffusion coefficient based on concentration data obtained from gas chromatographic analyses. The effects of the diffusion phenomenon were also investigated by Shore A hardness and scanning electron microscope (SEM) techniques. These analyses were carried out using samples aged at room temperature and at 80 °C. The hardness results showed an increasing trend for the samples aged at room temperature; however in the tests carried out at 80 °C they showed the opposite trend. The SEM analyses detected meaningful changes in the surface morphology of the propellant for both aging temperatures.

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Thermal characterization of glycidyl azide polymer (GAP) and GAP-based binders for composite propellants

Selim

Özkâr

Yılmaz

2000

J. Appl. Polym. Sci.

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Differential scanning calorimetry (DSC) and thermal gravimetric analysis (TGA) were used to investigate the thermal behavior of glycidyl azide polymer (GAP) and GAP-based binders, which are of potential interest for the development of highperformance energetic propellants. The glass transition temperature (T g ) and decomposition temperature (T d ) of pure GAP were found to be Ϫ45 and 242°C, respectively. The energy released during decomposition (⌬H d ) was measured as 485 cal/g. The effect of the heating rate on these properties was also investigated. Then, to decrease its T g , GAP was mixed with the plasticizers dioctiladipate (DOA) and bis-2,2-dinitropropyl acetal formal (BDNPA/F). The thermal characterization results showed that BDNPA/F is a suitable plasticiser for GAP-based propellants. Later, GAP was crosslinked by using the curing agent triisocyanate N-100 and a curing catalyst dibuthyltin dilaurate (DBTDL). The thermal characterization showed that crosslinking increases the T g and decreases the T d of GAP. The T g of cured GAP was decreased to sufficiently low temperatures (Ϫ45°C) by using BDNPA/F. The decomposition reaction-rate constants were calculated. It can be concluded that the binder developed by using GAP/N-100/ BDNPA/F/DBTDL may meet the requirements of the properties that makes it useful for future propellant formulations.

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Rocket Propulsion Elements

Cited by 827 publications

References 0 publications

Optimal design of a composite propellant formulation using response surface methodology

Optimal design of a composite propellant formulation using response surface methodology

Diffusion of plasticizer in a solid propellant based on hydroxyl-terminated polybutadiene

Thermal characterization of glycidyl azide polymer (GAP) and GAP-based binders for composite propellants

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