Gaseous Oxygen Injection Effects in Hybrid Labscale Rocket Motor Operations

Gomes, Susane R.; Rocco, Leopoldo; Rocco, José Atílio Fritz Fidel; Iha, Koshun

doi:10.2514/6.2010-6545

Cited by 7 publications

(3 citation statements)

References 1 publication

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“…3 Professor, Chemistry Department, friz@ita.br , AIAA Senior Member. 4 Professor, Chemistry Department, koshun@ita.br , AIAA Senior Member. encompassed the development of a polyurethane binder, or polymeric matrix, with total substitution of HTPB prepolymer for another polyol, or mix of polyols.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of polyurethane binder additivated with paraffin and tested with a swirl injector

Gomes¹,

Rocco²,

Rocco³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The fuel was synthesized with polyurethane (binder) based on pre-polymer technology modified with castor oil with the addition of 30% of paraffin and 10% of aluminum powder. An axial and a swirl injector were used. The regression rates doubled with the addition of paraffin and the mechanical properties increased drastically. Thrust measurements indicate that the addition of paraffin increased thrust at about 57% and regression rates at about 70%. The mixture that produced the best ballistic parameters was polyurethane plasticized with castor oil and 30% w/w of paraffin with gaseous oxygen injected with a swirler. The swirl injector improved the efficiency and regression rate values. Nomenclatureaverage oxidizer propellant mass flux rate Isp = specific Impulse n = regression rate exponent mሶ = fuel mass flow rate mሶ ୭୶ = oxidizer mass flow rate ‫ݎ‬ሶ ̅ = average regression rate of the solid fuel

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Section: Introductionmentioning

confidence: 99%

Evaluation of polyurethane binder additivated with paraffin and tested with a swirl injector

Gomes¹,

Rocco²,

Rocco³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

Self Cite

View full text Add to dashboard Cite

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“…In this way, it is possible to achieve high values of regression rate and efficiency. Several researchers tested various types of swirl injection, among which were Knuth et al [1][2][3], Yuasa et al [4], Masugi et al [5], Myre et al [6], and Gomes et al [7].…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Investigation of Unidirectional Vortex Injection in Hybrid Rocket Engines

Bellomo

Barato

Faenza

et al. 2013

Journal of Propulsion and Power

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A study on vortex injection in hybrid rocket engines with nitrous oxide and paraffin has been performed. The investigation followed two paths: first, the flowfield was simulated with a commercial computational fluid dynamics code; then, burn tests were performed on a laboratory-scale rocket. The computational fluid dynamics analysis had the dual purpose to help the design of the laboratory motor and to understand the physics underlying the vortex flow coupled with the combustion process compared with axial injection. Vortex injection produces a more diffuse flame in the combustion chamber and improves the mixing process of the reactants, both aspects concurring to increase the c efficiency. A helical streamline develops downstream of the injection region, and the pitch is highly influenced by combustion, which straightens the flow due to the acceleration in the axial direction imposed by the temperature rise. Experimental tests with similar geometry have been performed. Measured performance shows an increase in regression rate up to 51% and a c efficiency that rises from less than 80% with axial injection up to more than 90% with vortex injection. Moreover, a reduction of the instabilities in the chamber pressure has been measured. Nomenclature A t= nozzle throat area a = multiplication coefficient for regression rate G ox = mass flux in combustion chamber L g = grain length M f = mass of burned fuel M m = molar mass _ m tot = mean total mass flow n = exponential coefficient for regression rate O∕F = oxidizer to fuel mass ratio p, pc = pressure, mean chamber pressure R u = universal gas constant r = radial coordinate T = temperature t = time u r , u z , u θ = radial, tangential, and axial velocity z = axial coordinate μ = dynamic viscosity ρ f = density of fuel ρ = density ϕ i , ϕ e , ϕ m = initial, final, and mean diameter of the grain ω = vortex angular velocity

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“…However, in most cases, the gaseous oxygen is used due to its accessibility, handleability, and oxidizer's mass ow rate measurement [13][14][15]. To the best of the authors' knowledge, only a few number of scienti c sources have been devoted to the use of N 2 O in open literature, despite its wide usage in the propulsion applications.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of Fuel Regression Rate in a HTPB/N2O Hybrid Rocket Motor

2017

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Abstract. The performance of an HTPB/N2O hybrid motor was experimentally investigated. A hybrid motor was designed and manufactured in a laboratory with the purpose of studying the e ects of various parameters on the motor's performance, including fuel regression rate and speci c impulse. A series of tests were conducted to nd a correlation between the fuel regression rate and the oxidizer's mass ux. The e ects of chamber's pressure on the regression rate as well as other performance parameters were investigated. While the burning rate did not change dramatically, both the e ciency and ISP of the motor increased. The local fuel regression rate and the fuel port were also calculated. In addition, instantaneous regression rate was calculated using a special technique.

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Gaseous Oxygen Injection Effects in Hybrid Labscale Rocket Motor Operations

Cited by 7 publications

References 1 publication

Evaluation of polyurethane binder additivated with paraffin and tested with a swirl injector

Evaluation of polyurethane binder additivated with paraffin and tested with a swirl injector

Numerical and Experimental Investigation of Unidirectional Vortex Injection in Hybrid Rocket Engines

Experimental Study of Fuel Regression Rate in a HTPB/N2O Hybrid Rocket Motor

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