Optimization of Hybrid Propellant Mars Ascent Vehicle

Casalino, Lorenzo; Pastrone, Dario Giuseppe

doi:10.2514/6.2014-3953

Cited by 11 publications

(4 citation statements)

References 16 publications

(18 reference statements)

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“…The payload can yield around 13 tons for the manned mission and around 86 kg in the case of the sample return. These payload values are similar to those achieved by comparable liquid engine designs while being less expensive and simpler [11,31].…”

Section: Planetary and Lunar Lander Or Ascent Vehiclessupporting

confidence: 78%

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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 Vehiclessupporting

confidence: 78%

“…Casalino et al [11,31] proved the theoretical feasibility of a hybrid Mars sample return rocket and a manned return mission to a 170 km orbit. The payload can yield around 13 tons for the manned mission and around 86 kg in the case of the sample return.…”

Section: Planetary and Lunar Lander Or Ascent Vehiclesmentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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“…In Ref. [43] the authors analyzed a two-stage vehicle for the return of samples from Mars' surface and for a manned mission. A cluster of engines is used in the first stage, whereas a single HRE powers the second stage.…”

Section: Mars Ascent Vehiclementioning

confidence: 99%

Hybrid Rocket Engine Design Optimization at Politecnico di Torino: A Review

2021

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Optimization of Hybrid Rocket Engines at Politecnico di Torino began in the 1990s. A comprehensive review of the related research activities carried out in the last three decades is here presented. After a brief introduction that retraces driving motivations and the most significant steps of the research path, the more relevant aspects of analysis, modeling and achieved results are illustrated. First, criteria for the propulsion system preliminary design choices (namely the propellant combination, the feed system and the grain design) are summarized and the engine modeling is presented. Then, the authors describe the in-house tools that have been developed and used for coupled trajectory and propulsion system design optimization. Both deterministic and robust-based approaches are presented. The applications that the authors analyzed over the years, starting from simpler hybrid powered sounding rocket to more complex multi-stage launchers, are then presented. Finally, authors’ conclusive remarks on the work done and their future perspective in the context of the optimization of hybrid rocket propulsion systems are reported.

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“…An indirect procedure also underlies the well-known DUKSUP optimization software [2], which has been extensively employed by NASA in the design of the Atlas, Titan, and Space Shuttle launch systems. More recent work based on the indirect method includes both pure trajectory design applications [3][4][5] and closed-loop guidance algorithms [6][7][8]. However, when dealing with real-world launch vehicle missions, the indirect method may be unappealing as it requires the derivation of the optimality conditions, which can be a burdensome task, and the solution of the resulting boundary value problem requires a meticulous initialization process to achieve convergence.…”

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confidence: 99%