Regression Rate Enhancement of Hybrid Rockets by Introducing Novel Distributed Tube Injector

Kahraman, Mehmet; Özkol, İbrahim; Karabeyoğlu, M. Arif

doi:10.2514/1.b38417

Cited by 11 publications

(3 citation statements)

References 8 publications

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“…Since the DTI is in the center of the fuel grain and, thus, subject to high combustion temperatures, the material choice was critical. The best performance (in terms of both cost and durability) yielded stainless steel with a nylon protective sleeve [92]. In experiments, using N 2 O as oxidizer, the regression rate could be increased by 3.9 times as compared to the reference case with the motor with only head-end injection and in many cases the combustion efficiency increased too.…”

Section: Distributed or Multi-segment Injectionmentioning

confidence: 98%

“…As a second example of distributed injection, two concepts that are similar are presented. The Beihang University [90,91] and Kahraman et al [92] propose another method to distribute the injector effects along the whole fuel grain rather than only at the head-end. The concept is labeled double tube by Beihang University and Distributed Tube Injector (DTI) by Kahraman et al.…”

Section: Distributed or Multi-segment Injectionmentioning

confidence: 99%

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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: Distributed or Multi-segment Injectionmentioning

confidence: 98%

Section: Distributed or Multi-segment Injectionmentioning

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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show abstract

“…Taken from [5] with permission. References (from top to bottom): AIEB [119], Bi-vortex [120], AP + Ferric oxide [121], Helical grain [122], Bluff body [123], Paraffin [124], DTI [125], GAP [126], Multi section swirl [127], Expandable graphite [128], Aluminium hydride [129], Head-end swirl [130], CAMUI fuel port [131], Double tube [132], Two section swirl [133], Concave-convex [134], Armoured grain [58], Diaphragm (4 hole) [135], Amorphous aluminium [136], 5-stepped fuel [137], Vortex injection [138], Single step [139], Single diaphragm [140], Carbon nano tubes [141], Carbon black [142], Transition metal [143], Multi segmented grain [144], Hollow cone injector [145], Nested helix [59].…”

mentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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Hybrid rocket propulsion, first demonstrated by the Russian GIRD-09 rocket in 1933, combines liquid oxidizer and solid fuel for thrust generation. Despite numerous advantages, such as enhanced safety, controllability, and potential environmental benefits, hybrid propulsion has yet to achieve its full potential in space applications. In recent years, the research on hybrid propulsion has gained enormous momentum in both academia and industry. Recent accomplishments such as the altitude record for student rockets (64 km), the launch of the first electric pump-fed hybrid rocket, and a successful 25 s hovering test highlight the potential of hybrid rockets. However, although the hybrid community is growing constantly, industrial utilizations and in-space validations do not yet exist. In this work, we reassess the possibilities of hybrid rocket engines by presenting potential fields of applications from the literature. Most importantly, we identify the technical challenges that hinder the breakthrough of hybrid propulsion in the space sector and evaluate the technologies and approaches necessary to bridge the gaps in hybrid rocket development.

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Hybrid regression rate data

Chandler Karp,

Jens

2024

Hybrid Rocket Propulsion Design Handbook

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Regression Rate Enhancement of Hybrid Rockets by Introducing Novel Distributed Tube Injector

Cited by 11 publications

References 8 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

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Hybrid regression rate data

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