Performance and Regression Rate Characteristics of 5-kN Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine

Sakurai, Takashi; Yuasa, Saburo; Ando, Hiromitsu; Kitagawa, Koki; Shimada, Toru

doi:10.2514/1.b36239

Cited by 21 publications

(7 citation statements)

References 13 publications

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“…Burn tests reporting regression rates up to 2.7 times higher. The team surrounding the researchers continued on the swirl injection method (named SOFT: Swirling-Oxidizer-Flow-Type), continuously progressing the idea [73,74] for a potential application in an economic hybrid launch vehicle for Japan [75]. The conclude this section, the last type of head-end injection methods are introduced: The Axial-Injection End-Burning-or AIEB-designs (not to confuse with the end-burning radial injection designs in Sect.…”

Section: Head-end Injection Methodsmentioning

confidence: 99%

Evaluation of Regression Rate Enhancing Concepts and Techniques for Hybrid Rocket Engines

Glaser

Hijlkema

Anthoine

2022

Aerotec. Missili Spaz.

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The low regression rate of Hybrid Rocket Engines (HREs) is one prominent characteristic that is addressed in most abstracts concerning hybrid propulsion. Over the years, researchers developed and investigated numerous ways to tackle the low regression rate problem of HREs. This article is a collection and assessment of these diverse methods and designs. It allows for a quick overview of the different mechanisms that are being employed and can serve both as information and inspiration. The enhancement ideas are grouped together as (a) adjustments to the solid fuel chemical properties, (b) advanced injection methods and concepts and (c) improving the combustion chamber design. These different techniques are discussed and their individual impact on the regression rate is assessed both qualitatively and quantitatively. All methods that are presented come with a different set of advantages and disadvantages, making the regression rate enhancement a trade-off problem. In our view, the most promising designs and methods are those that only call for minor adjustments to the HRE design, as they can be also added to already existing engines. Above all, it is to be said that regression rate enhancing techniques that change the unique features of HREs (namely safety, simplicity and low cost) are to be employed with caution. Only if the achievable regression rate increase is justifying the implications for the HRE in the envisioned use-case, these concepts represent promising alternatives to the status quo.

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Section: Head-end Injection Methodsmentioning

confidence: 99%

Evaluation of Regression Rate Enhancing Concepts and Techniques for Hybrid Rocket Engines

Glaser

Hijlkema

Anthoine

2022

Aerotec. Missili Spaz.

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“…Aerospace 2023, 10, x FOR PEER REVIEW 18 of 28 The authors proposed the following fuel regression rate correlations for the SOFT hybrid rocket engines [49]:…”

Section: Time-averaged Engine Performance and Fuel Regression Rate Co...mentioning

confidence: 99%

Experimental Investigation of a Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine Using Low-Melting-Point Thermoplastic Fuel and Oxygen

2023

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Hybrid rockets are safe and inexpensive; however, boundary-layer combustion poses a problem in achieving a fuel regression rate equivalent to that of solid propellants. The fundamental combustion conditions, such as the fuel regression rate of LT421, a paraffin-based low-melting-point thermoplastic fuel, were investigated using a swirling-flow combustion method. Firing tests were conducted using the oxygen mass flow rate and burn time parameters. The LT fuel exhibited an ignition delay compared to polypropylene, and the pressure increased slowly relative to the thrust. The combustion pressure increased or remained constant with time, suggesting that the fuel regression rate was more dependent on the oxygen mass flow rate than the oxidizer mass flux. The shear force generated in the grain owing to the swirling flow caused fuel-grain separation when the oxygen mass flow rate exceeded 100 g/s. Fuel-grain separation was prevented by modifying the case geometry. The maximum fuel regression rate obtained in the tests was 4.88 mm/s at an oxygen mass flow rate of 190 g/s and mass flux of 72.4 kg/(m2s), which was four times higher than that of polypropylene at the same oxidizer mass flux. The fuel regression rate correlation was obtained using the oxygen mass-flow-rate-based parameter, although further modification was necessary to apply this correlation when the burning time was varied.

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“…31) This includes the work on a 5 kN swirling oxidizer flow hybrid rocket engine. 32) Space-ShipOne and SpaceShipTwo are still the most well-known examples of flight proven hybrid rocket engines. A sub-orbital hybrid sounding rocket is in development by the Norwegian company NAMMO.…”

Section: Recent and Current Programsmentioning

confidence: 99%

A Record Flight of the Hybrid Sounding Rocket HEROS 3

Kobald¹,

Schluechter²,

Fischer³

et al. 2018

AEROSPACE TECHNOLOGY JAPAN

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Hybrid rocket propulsion offers inherent safety during handling and launch operations at low cost. This makes it not only attractive for space tourism applications like SpaceShipTwo but also for sounding rockets and for educational activities with students. This has been successfully demonstrated by the HyEnD student project from the University of Stuttgart: On November 8 th , 2016 at 10:30 a.m. the hybrid sounding rocket HEROS 3 was launched from the Esrange Space Center to an apogee altitude of 32,300 m (106,000 ft). This set a new altitude record for European student and amateur rocketry. Furthermore, this is a world altitude record for hybrid rockets built by students. It was successfully recovered with the drogue and main parachute being released. The rocket was powered by a 10 kN design thrust hybrid rocket engine with a paraffin-based fuel and Nitrous Oxide (N 2 O) as the oxidizer. The combustion efficiency was verified to be above 97 % in ground tests. Liquid burn time in the flight was for 15 s with an additional combustion of gaseous N 2 O in the blow-down mode of about 10 s. The rocket was 7.5 m long with an empty mass of about 75 kg. The rocket structure was made completely from light-weight carbon fibre and glass fibre reinforced plastic.

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Performance and Regression Rate Characteristics of 5-kN Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine

Cited by 21 publications

References 13 publications

Evaluation of Regression Rate Enhancing Concepts and Techniques for Hybrid Rocket Engines

Evaluation of Regression Rate Enhancing Concepts and Techniques for Hybrid Rocket Engines

Experimental Investigation of a Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine Using Low-Melting-Point Thermoplastic Fuel and Oxygen

A Record Flight of the Hybrid Sounding Rocket HEROS 3

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