A new strategy for the reinforcement of paraffin-based fuels based on cellular structures: The armored grain — Ballistic characterization

Bisin, Riccardo; Paravan, Christian

doi:10.1016/j.actaastro.2023.02.027

Cited by 13 publications

(15 citation statements)

References 65 publications

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“…In recent years, three-dimensional (3D) printing technology has become sufficiently developed and successfully applied to the manufacturing of hybrid rocket fuel grains [25][26][27][28][29][30][31][32]. This technique allows for direct integral molding of polymeric fuel grains with a complex single port, which is difficult to accomplish using traditional manufacturing methods [25].…”

Section: Introductionmentioning

confidence: 99%

“…Paraffin-based fuels have gained significant attention due to their high regression rates, despite their poor mechanical properties. Embedding 3D printed skeletons, such as the "armored grain" proposed by Bisin et al [28,29], enhanced the mechanical properties of the paraffin-based grains at the expense of regression rate. In the work of our group, both mechanical properties as well as the regression rate of paraffin-based fuels with embedded ABS helical structure framework proposed by Wang et al [30] were significantly improved.…”

Section: Introductionmentioning

confidence: 99%

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Regression Rate and Combustion Efficiency of Composite Hybrid Rocket Grains Based on Modular Fuel Units

Pan,

Lin,

Wang

et al. 2024

Aerospace

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This study investigated combustion characteristics of composite fuel grains designed based on a modular fuel unit strategy. The modular fuel unit comprised a periodical helical structure with nine acrylonitrile–butadiene–styrene helical blades. A paraffin-based fuel was embedded between adjacent blades. Two modifications of the helical structure framework were researched. One mirrored the helical blades, and the other periodically extended the helical blades by perforation. A laboratory-scale hybrid rocket engine was used to investigate combustion characteristics of the fuel grains at an oxygen mass flux of 2.1–6.0 g/(s·cm2). Compared with the composite fuel grain with periodically extended helical blades, the modified composite fuel grains exhibited higher regression rates and a faster rise of regression rates as the oxygen mass flux increased. At an oxygen mass flux of 6.0 g/(s·cm2), the regression rate of the composite fuel grains with perforation and mirrored helical blades increased by 8.0% and 14.1%, respectively. The oxygen-to-fuel distribution of the composite fuel grain with mirrored helical blades was more concentrated, and its combustion efficiency was stable. Flame structure characteristics in the combustion chamber were visualized using a radiation imaging technique. A rapid increase in flame thickness of the composite fuel grains based on the modular unit was observed, which was consistent with their high regression rates. A simplified numerical simulation was carried out to elucidate the mechanism of the modified modular units on performance enhancement of the composite hybrid rocket grains.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Regression Rate and Combustion Efficiency of Composite Hybrid Rocket Grains Based on Modular Fuel Units

Pan,

Lin,

Wang

et al. 2024

Aerospace

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“…The addition of small amounts of additives increases the strength and ductility of paraffin wax but increases the viscosity coefficient, which often results in lower fuel regression rates. Another method comprises the reinforcement of the mechanical properties of paraffin wax using additive manufacturing [27][28][29][30]. The mechanical and combustion properties of paraffin wax fuel are balanced by the reinforcement structure.…”

Section: Introductionmentioning

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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“…There are, however, additives that can increase the mechanical properties while impacting the liquid fuel layer; an extensive review can be found in [56]. Moreover, embedded structures such as armoured grain [57,58] or nested helix [59] can simultaneously increase both the structural integrity and regression rate. Furthermore, recent achievements such as large-scale tests and launches of paraffin-fuelled hybrid rockets (see Section 3.12) show that these problems can be effectively tackled.…”

mentioning

confidence: 99%

“…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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A new strategy for the reinforcement of paraffin-based fuels based on cellular structures: The armored grain — Ballistic characterization

Cited by 13 publications

References 65 publications

Regression Rate and Combustion Efficiency of Composite Hybrid Rocket Grains Based on Modular Fuel Units

Regression Rate and Combustion Efficiency of Composite Hybrid Rocket Grains Based on Modular Fuel Units

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

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

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