Combustion characteristics of hybrid rocket motor with segmented grain

Tian, Hui; Sun, Xiaofeng; Guo, Yudong; Wang, Pengfei

doi:10.1016/j.ast.2015.08.009

Cited by 37 publications

(8 citation statements)

References 5 publications

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“…15. Experiments ( H 2 O 2 ∕PE ) with the smallest configuration (first fuel block has one fuel port, second fuel block has three ports) yielded a total regression rate increment of around 13% and the combustion efficiency increased by around 10% [142]. More detailed, the regression rate in the first block (a classic cylindrical fuel) did not change, while the second block experienced regression rates around 20% higher.…”

Section: Advanced Fuel Port Profiles and Combustion Chambersmentioning

confidence: 94%

“…Exploiting a similar effect of numerous fuel segments with multiple ports that are rotated relative to each other, Tian et al [142,143] presented a multi segmented grain. In this concept, neither the relative angular displacement nor the number of fuel ports for each segment is fixed.…”

Section: Advanced Fuel Port Profiles and Combustion Chambersmentioning

confidence: 99%

“…Moreover, higher temperatures promote the production Fig. 15 Multi-segmented grain (based on [142]) of OH* an O* radicals that react with the graphite of the nozzle [144].…”

Section: Mixture Ratiomentioning

confidence: 99%

See 2 more Smart Citations

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: Advanced Fuel Port Profiles and Combustion Chambersmentioning

confidence: 94%

Section: Advanced Fuel Port Profiles and Combustion Chambersmentioning

confidence: 99%

See 1 more Smart Citation

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

Glaser

Hijlkema

Anthoine

2022

Aerotec. Missili Spaz.

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“…En la parte de simulación, se obtiene la eficiencia de la combustión y las distribuciones de la tasa de regresión, la temperatura y la fracción de masa de las especies en los casos de granos segmentados. Las pruebas correspondientes son realizadas por el motor a escala de laboratorio con 90 % de H 2 O 2 y combinación de propelente de PE [26].…”

Section: Descripci óNunclassified

Solar Thermal Water Splitting

Roeb

Monnerie

Houaijia

et al. 2013

Renewable Hydrogen Technologies

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“…Cylindrical grain and slotted grain designs of varying practicality and complexity were optimized using a sounding rocket internal ballistic optimization strategy. They discussed the applications of star grains which includes the benefit is the possibility of a neutral-regressive burn to attain maximum efficiency and thus together maximize flight characteristics and performance of a rocket (Hainline, 2006; Tian et al , 2015; Pal et al , 2012; Adrian-Nicolae Buturache, 2018). Design and optimization of a slotted star grain design is known for its reliability, efficiency and simplicity for a ballistic requirement of rocket performance (Rafique, 2015; Hainline, 2006).…”

Section: Introductionmentioning

confidence: 99%

Regression rate performance of paraffin wax and bees wax –Gox with varied grain configuration in a hybrid rocket motor

Saravanan

Shanmugam

Veerappan

2021

AEAT

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Purpose This paper aims to determine the regression rate using wax fuels for three different grain configurations and find a suitable grain port design for hybrid rocket application. Design/methodology/approach The design methodology of this work includes different grain port designs and subsequent selection of solid fuels for a suitable hybrid rocket application. A square, a cylindrical and a five-point star grained were designed and prepared using paraffin and beeswax fuels. They were tested in a laboratory-scale rocket with gaseous oxygen to study the effectiveness of solid fuels on these grain structures. The regression rate by static fire testing of these wax fuels was analyzed. Findings Beeswax performance is better than that of paraffin wax fuel for all three designs, and the five-slotted star fuel port grain attained the best performance. Beeswax fuel attained an average regression rate ≈of 1.35 mm/s as a function of oxidizer mass flux Gox ≈ 111.8 kg/m2 s and for paraffin wax 1.199 mm/s at Gox ≈ 121 kg/m2 s with gaseous oxygen. The local regression rates of fuels increased in the range of 0.93–1.194 mm/s at oxidizer mass flux range of 98–131 kg/m2 s for cylindrical grain, 0.99–1.21 mm/s at oxidizer mass flux range of 96–129 kg/m2s for square grain and 1.12–1.35 mm/s at oxidizer mass flux range of 91–126 kg/m2 s for a star grain. A complete set of the regression rate formulas is obtained for all three-grain designs as a function of oxidizer flux rate. Research limitations/implications The experiment has been performed for a lower chamber pressure up to 10 bar. Originality/value Different grain configurations were designed according to the required dimension of the combustion chamber, injector and exhaust nozzle of the design of a lab-scale hybrid rocket, and input parameters were selected and analyzed.

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Combustion characteristics of hybrid rocket motor with segmented grain

Cited by 37 publications

References 5 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

Solar Thermal Water Splitting

Regression rate performance of paraffin wax and bees wax –Gox with varied grain configuration in a hybrid rocket motor

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