Development of a small sounding hybrid rocket with a swirling-oxidizer-type engine

Yuasa, Saburo; Yamamoto, Kengo; Hishida, Hitoshi; Kitagawa, Koki; Oowada, Youichi

doi:10.2514/6.2001-3537

Cited by 71 publications

(41 citation statements)

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“…It is, however, generally known that the effect of swirl flow is only limited near the inlet part of the fuel port because swirl strength diminishes by the viscous interaction with the solid fuel surface as it flows downstream. A typical example of combustion with swirl flow in hybrid fuel can be found in reference [3]. So it is natural to seek a method not only to minimize the disadvantage of the swirl injector but to overcome the negative effects by using other options.…”

Section: Methodsmentioning

confidence: 99%

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Internal Flow Dynamics and Regression Rate in Hybrid Rocket Combustion

Lee¹

2012

International Journal of Aeronautical and Space Sciences

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The present study is the analyses of what has been attempted and what was understood in terms of improving the regression rate and enlarging the basic understanding of internal flow dynamics. The first part is mainly intended to assess the role of helical grain configuration in the regression rate inside the hybrid rocket motor. To improve the regression rate, a combination of swirl (which is an active method) and helical grain (which is a passive method) was adopted. The second part is devoted to the internal flow dynamics of hybrid rocket combustion. A large eddy simulation was also performed with an objective of understanding the origin of isolated surface roughness patterns seen in several recent experiments. Several turbulent statistics and correlations indicate that the wall injection drastically changes the characteristics of the near-wall turbulence. Contours of instantaneous streamwise velocity in the plane close to the wall clearly show that the structural feature has been significantly altered by the application of wall injection, which is reminiscent of the isolated roughness patterns found in several experiments.

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Section: Methodsmentioning

confidence: 99%

“…The swirl flow can also increase the residence time (or contact time) of the oxidizer stream with the fuel surface. Yuasa et al [3] designed several swirl injectors and tested the effect of swirl strength on the regression rate. Their results revealed that the average regression rate increases up to 200% as the swirl number increases.…”

Section: Introductionmentioning

confidence: 99%

Internal Flow Dynamics and Regression Rate in Hybrid Rocket Combustion

Lee¹

2012

International Journal of Aeronautical and Space Sciences

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“…a side burning grain. A regression rate about 2.7 greater than that for classical axial flow hybrid rockets was found, for a motor using PMMA as fuel burning with gaseous O 2 as oxidizer [18,67,71,73].…”

Section: Swirl Injection In Side-burning Grainsmentioning

confidence: 99%

Scaling of Hybrid Rocket Motors with Swirling Oxidizer Injection

Paccagnella¹,

Karabeyoğlu²,

Barato³

et al. 2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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“…a and n in Eq. (1) are determined from the experiment for a nonswirling oxidizer with the WAX fuel In this study, a swirling-oxidizer-type HRE, which can achieve a higher regression rate, 4) is assumed. For this purpose, the empirical multiplication with the coefficient of Eq.…”

Section: Procedures For Hre Performance Evaluationmentioning

confidence: 99%

Multi-Stage Hybrid Rocket Conceptual Design for Micro-Satellites Launch using Genetic Algorithm

Kitagawa

Nakamiya

et al. 2012

Trans. Japan Soc. Aero. S Sci.

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The multi-objective genetic algorithm (MOGA) is applied to the multi-disciplinary conceptual design problem for a three-stage launch vehicle (LV) with a hybrid rocket engine (HRE). MOGA is an optimization tool used for multiobjective problems. The parallel coordinate plot (PCP), which is a data mining method, is employed in the post-process in MOGA for design knowledge discovery. A rocket that can deliver observing micro-satellites to the sun-synchronous orbit (SSO) is designed. It consists of an oxidizer tank containing liquid oxidizer, a combustion chamber containing solid fuel, a pressurizing tank and a nozzle. The objective functions considered in this study are to minimize the total mass of the rocket and to maximize the ratio of the payload mass to the total mass. To calculate the thrust and the engine size, the regression rate is estimated based on an empirical model for a paraffin (FT-0070) propellant. Several non-dominated solutions are obtained using MOGA, and design knowledge is discovered for the present hybrid rocket design problem using a PCP analysis. As a result, substantial knowledge on the design of an LV with an HRE is obtained for use in space transportation.

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Development of a small sounding hybrid rocket with a swirling-oxidizer-type engine

Cited by 71 publications

References 1 publication

Internal Flow Dynamics and Regression Rate in Hybrid Rocket Combustion

Internal Flow Dynamics and Regression Rate in Hybrid Rocket Combustion

Scaling of Hybrid Rocket Motors with Swirling Oxidizer Injection

Multi-Stage Hybrid Rocket Conceptual Design for Micro-Satellites Launch using Genetic Algorithm

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