The regolith rocket—A hybrid rocket using lunar resources

Stoll, Enrico; Härke, Philip; Linke, Stefan; Heeg, Francesca; May, Stefan

doi:10.1016/j.actaastro.2020.11.022

Cited by 11 publications

(4 citation statements)

References 12 publications

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“…For lunar applications, in situ utilization of regoliths has been researched as well. For example, Stoll et al [26] investigated the use of oxygen as oxidizer, aluminium (as pure metal fuel) from regoliths, and alloys for tanks and fairings. The combustion of pure metal fuels is assumed to be possible, though with performance losses.…”

Section: Planetary and Lunar Lander Or Ascent Vehiclesmentioning

confidence: 99%

“…The combustion of pure metal fuels is assumed to be possible, though with performance losses. Stoll et al [26] showed that it is theoretically possible to insert 500 kg into a 300 km lunar orbit using fuel, oxidizer tanks, and fairings from lunar regoliths (using 349.1 kg material from earth and 1410 kg in situ material). This could be a use case for a future lunar gateway.…”

Section: Planetary and Lunar Lander Or Ascent Vehiclesmentioning

confidence: 99%

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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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Section: Planetary and Lunar Lander Or Ascent Vehiclesmentioning

confidence: 99%

Section: Planetary and Lunar Lander Or Ascent Vehiclesmentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

View full text Add to dashboard Cite

show abstract

“…They have received considerable attention in studies on space missions due to their safety, easily controlled thrust, on-demand restart capability, and low cost [1,2]. They also play a supporting role in missions involving space transportation [3,4], manned lunar landings [5,6], and Mars vehicles [7,8]. The control of hybrid rocket motors thus warrants further research, especially from the perspectives of their specific impulse performance and accuracy of thrust control.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation into Closed-Loop Control for HTPB-Based Hybrid Rocket Motors

et al. 2023

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Space exploration greatly facilitates the development of advanced propulsion systems. Extensive research has shown that hybrid rocket motors have bright prospects for use in variable-thrust propulsion systems. However, the variable-thrust precision control of a hybrid rocket motor with a high-mass fraction of aluminum has not been adequately explored. In this paper, we propose a closed-loop control system for a high-performance laboratory-scale hybrid rocket motor, and verify its performance through tests on a hybrid rocket motor containing 98% hydrogen peroxide and hydroxyl-terminated polybutadiene with 58% of an aluminum additive. The results show that, first, the average value of thrust in the stable sections in the three stages were 400.7 N, 599.1 N, and 400.1 N when the target values were 400 N, 600 N, and 400 N, respectively. Second, the average thrust was stable, and the control error of the average value was better than 0.5%. Third, the real-time error in thrust was controlled to within ± 20 N with a steady-state error smaller than 5%. These results indicate that the proposed closed-loop control strategy for hybrid rocket motors with a high-mass fraction of aluminum can maintain a constant thrust and smooth transitions in case of variable thrust.

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“…Its major constituent is oxygen [3] that can be utilized for both life support and propellant, the latter together with hydrogen either extracted or brought from Earth. Regolith itself can be used as raw material for 3D printing [4], and even for hybrid rockets construction [5]. The incorporation of ISRU capabilities can provide multiple benefits for exploration activities, as it implies mass, cost and risk reduction, together with increased flexibility [6,7].…”

Section: Introductionmentioning

confidence: 99%