Experimental and Numerical Investigations for the Combustion of Selected Composite Solid Propellant

Hegab, A.; A.M., Hasanien; S.A., Mostafa; Maraden, H. E.

doi:10.21608/erjm.2012.67173

Cited by 1 publication

(1 citation statement)

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“…In order to have a stable rocket system with desirable performance, individual study for the combustion model that incorporates the burning of microscale propellant and the nonreactive model that accounts the complex fluid flow inside the chamber and the nozzles must be examined first. Some recent studies that consider the burning of microscale solid rocket propellant [1][2][3][4][5][6] concluded that the injection conditions of the cold models in [7][8][9][10][11][12][13][14] are found to be different than that considered with the reactive models [1][2][3][4][5][6]. As a result, the current study is conducted to examine the unsteady flow field inside the solid rocket motor chamber and the complex generated wave and vorticity patterns and their impact on the burning of real solid propellant surfaces.…”

Section: Introductionmentioning

confidence: 99%

Impact of the Surface Morphology on the Combustion of Simulated Solid Rocket Motor

Hegab

Sait

Hussain

2015

Mathematical Problems in Engineering

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An advanced and intensive computational solution development is integrated with an asymptotic technique, to examine the impact of the combustion surface morphology on the generated rotational flow field in a solid rocket chamber with wide ranges of forcing frequencies. The simulated rectangular chamber is closed at one end and is open at the aft end. The upper and lower walls are permeable to allow steady and unsteady injected air to generate internal flow mimicking the flow field of the combustion gases in real rocket chamber. The frequencies of the unsteady injected flow are chosen to be very close or away from the resonance frequencies of the adapted chamber. The current study accounts for a wide range of wave numbers that reflect the complexity of real burning processes. Detailed derivation for Navier-Stokes equations at the four boundaries of the chamber is introduced in the current study. Qualitative comparison is performed with recent experimental work carried out on a two-inch hybrid rocket motor using a mixture of polyethylene and aluminum powder. The higher the percentage of aluminum powder in the mixture, the more the corrugations of the combustion surface. This trend is almost similar to the computational and analytical results of a simulated solid rocket chamber.

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