Internal ballistic considerations in hybrid rocket design.

Muzzy, R. J.; Wooldridge, C. E.

doi:10.2514/3.28844

Cited by 45 publications

(14 citation statements)

References 9 publications

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“…Kosdon and Williams [24] later noted that Miller's analysis was only applicable to systems with low pressure and moderate oxidizer fluxes and derived a new expression that incorporated a flame zone of finite thickness. Wooldridge and Muzzy [25] examined the effects of scaling and pressure on motor performance in the context of throttling. In his 1972 article, Muzzy [26] pointed out that even simple PMMA-O 2 motors behaved differently at low pressures and that as the motor approached a flooding condition, combustion likely became kinetically-limited.…”

Section: Kinetics-limited Modelsmentioning

confidence: 99%

Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Marquardt

Majdalani

2019

Aerospace

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In this article, we undertake a concise review of several milestone developments in classical regression rate models of hybrid rocket motors. After a brief description of the physical processes entailed in hybrid rocket combustion, Marxman's diffusion-limited theory is re-constructed and discussed. Considerations beyond the scope of basic convection-driven models, which address disparate forms of the blowing correction, variable fluid properties, and pressure and radiation effects, are also given. Finally, a selection of kinetically-limited models is presented, with the aim of comparing the characteristics of several competing theories that become applicable under particular circumstances.

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Section: Kinetics-limited Modelsmentioning

confidence: 99%

Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Marquardt

Majdalani

2019

Aerospace

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“…The total gas flow m g & can be described at any point of the gaseous stream of the combustion products, m g & = f(x), which is composed of the rate of head-end oxidizer flow plus the gas evolved from the surface minus the oxidizer consumed in the combustion. That can be describing by the following equations according to state of combustion [9]:…”

Section: Computer Programmentioning

confidence: 99%

Modeling of Metallized Solid Fuel Hybrid Propulsion System

Makled

Mostafa

Al-Sanabawy

et al. 2012

The International Conference on Applied Mechanics and Mechanica

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The most commonly used Hybrid Rocket Motor (HRM) consists of an inert pure solid fuel (SF) with liquid or gaseous oxidizer. Until now, the regression rate of SF in HRM has typically been an order of magnitude lower than that of solid propellant motor. The objective of this paper is to investigate the possible enhancement of regression rate by addition of metal powder. This may guide to effectively design and produce high performance HRM for specific applications. A mathematical model has been introduced and a computer program is built to describe metalized SF regression rate and HRM performance. A series of experimental tests using a small scale HRM employs Polyethylene (PE) with Aluminum (Al) metal powder additive (2.5, 5, 7.5, 10, 12.5, and 15% by mass) as SF and gaseous oxygen (GO2) as oxidizer to evaluate the metalized SF regression rate and HRM performance. The measured experimental data are compared with results obtained from theoretical computation. The comparison shows good agreement, which proves the validity of the developed program, since the maximum error noticed was generally less than 10%. An addition of up to 7.5% Al powder increases the regression rate by about 90% and the chamber pressure by nearly 40% as compared to classical HRM with no additives.

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“…The total gas flow can be described at any point of the gaseous stream of the combustion products, m = f(x), which is composed of the rate of head-end oxidizer flow plus the gas evolved from the surface minus the oxidizer consumed in the combustion. This can be described by the following equation [5].…”

Section: Effective Total Gas Flow Rate Parametermentioning

confidence: 99%

Prediction of Hybrid Combustion Boundary Layer Parameters

Makled

2007

International Conference on Aerospace Sciences and Aviation Tec

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The hybrid combustion phenomenon is more complex than the case of solid or liquid combustion. An understanding of hybrid combustion is dependent upon understanding of the interrelationships between the boundary layer zones characteristics and fuel grain geometry during burning time and along fuel grain. The main objectives of the article are to predict hybrid combustion boundary layer geometry and characteristic parameters variation with fuel grain length during combustion. Specially, the relation between flame zone (propagation) position and regression rate change values during combustion. Based on this mathematical model, a computer code was implemented to identify the hybrid combustion boundary layer (BL) parameters. The comparison between Schlieren photograph of Plexiglas-oxygen flat plate burner and computational results show good agreement. The presented code can be considered as a powerful tool for the design, analysis and can be used to evaluate quantitatively the effect of changes in various design parameters of hybrid rocket motor.

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Internal ballistic considerations in hybrid rocket design.

Cited by 45 publications

References 9 publications

Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Modeling of Metallized Solid Fuel Hybrid Propulsion System

Prediction of Hybrid Combustion Boundary Layer Parameters

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