Experimental Investigation of High-Burning-Rate Composite Solid Propellants

Manship, Timothy D.; Heister, Stephen D.; O'Neil, Patrick T.

doi:10.2514/1.b34559

Cited by 12 publications

(2 citation statements)

References 35 publications

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“…This increase in pressure exponent is likely due to more agglomerates less than 10 microns corresponding to kinetically limited combustion [51]. In contrast, non-energetic catalysts, such as iron oxide, can increase the burning rate by 1.5 to 2 times the original value depending on the size of catalyst particles and the amount added [52][53][54]. Because these catalysts do not contribute to the reaction's overall energy, there will also be a decrease in Isp.…”

Section: Combustion Experimentsmentioning

confidence: 99%

On the Use of Fluorine‐Containing Nano‐Aluminum Composite Particles to Tailor Composite Solid Rocket Propellants

Uhlenhake

Yehia

Noel

et al. 2022

Propellants Explo Pyrotec

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The burning rate of solid propellants is an important factor for optimizing rocket motors and improving performance. The enhanced burning rate can increase thrust and reduce a propulsion system's overall size and weight. In this study, a novel nano-aluminum/THV composite additive was prepared and introduced into a solid ammonium perchlorate/polybutadiene composite solid rocket propellant to enhance its burning rate. The morphology of the composite particle additive and its effects on combustion were characterized. The use of small quantities (< 15 wt.%) of the additive resulted in a burning rate enhancement of up to 2.1 times that of the conventional coarse aluminized propellant with a specific impulse loss of only 3 seconds, and as much as 4.7 times enhancement with a predicted loss of 22 seconds in theoretical specific impulse. Some of this loss may be recovered by the improved combustion efficiency in smaller rocket motors because the additive was shown to significantly reduce the aluminum agglomeration at the propellant burning surface and reduce the size of reaction products which may reduce two-phase flow losses. The additive also provides wide burning rate tailorability, favorable for motor, grain, and thrust curve design. The burning rate enhancement mechanism is thought to be a physical cratering mechanism governed by the burning rate disparity between the binder/oxidizer system and the nano-aluminum/fluoropolymer additive and not a chemical catalytic effect.

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Section: Combustion Experimentsmentioning

confidence: 99%

On the Use of Fluorine‐Containing Nano‐Aluminum Composite Particles to Tailor Composite Solid Rocket Propellants

Uhlenhake

Yehia

Noel

et al. 2022

Propellants Explo Pyrotec

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show abstract

“…Because to the high oxidant content of AP, its self-deflagration may be maintained at pressures more than 20 bar. Because fine AP burns quicker than coarse AP in propellants, the particle size distribution of AP has a considerable impact on burning rate tailoring [4][5].…”

Section: Introductionmentioning

confidence: 99%

Propulsion theoretical and experimental analysis of composite propellants motors

Said,

Maraden,

Elhedery

et al. 2023

J. Phys.: Conf. Ser.

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Rockets have revolutionized space technology and human space exploration. Most rockets and missiles are both propelled by rocket motors that use composite solid propellants. The ICT code and the NSAS CEA code are two programs that can be used to forecast theoretical propulsion parameters for composite solid rocket propellant. Rocket propellant performance is governed by a specific impulse factor, which is calculated theoretical and experiment. In this paper, the theoretical specific impulse for different composite solid propellant formulations at 70 bar combustion pressure and an adapted nozzle (optimum expansion) were calculated by the NASA-CEA code and the ICT code. Meanwhile, a static firing test was performed on a small scale test motor to experimentally determine the actual specific impulse. The objective is to verify theoretical calculations from two codes with experimental data, via the determination of the specific impulse deviation co-efficient.

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Facile energetic fluoride chemistry induced organically coated aluminum powder with effectively improved ignition and combustion performances

Zhang

Wang

et al. 2023

J Therm Anal Calorim

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Experimental Investigation of High-Burning-Rate Composite Solid Propellants

Cited by 12 publications

References 35 publications

On the Use of Fluorine‐Containing Nano‐Aluminum Composite Particles to Tailor Composite Solid Rocket Propellants

On the Use of Fluorine‐Containing Nano‐Aluminum Composite Particles to Tailor Composite Solid Rocket Propellants

Propulsion theoretical and experimental analysis of composite propellants motors

Facile energetic fluoride chemistry induced organically coated aluminum powder with effectively improved ignition and combustion performances

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