Hybrid propulsion for small satellites analysis and tests

Lengellé, G.; Foucaud, R.; Godon, J.; Heslouin, A.; Lecourt, Renaud; Maisonneuve, Yves; Pillet, Nicolas

doi:10.2514/6.1999-2321

Cited by 3 publications

(5 citation statements)

References 2 publications

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“…Markopoulos et al [19] have shown that adding two hybrid boosters to the ATLAS 2AR increases the payload capacity from 3900 kg (8600 lbs) in GTO to 4763 kg (10,500 lbs). Lengellé et al [20] stated that the replacement of the solid booster for Ariane 5 with a hybrid LOX/HTPB system would reduce its weight by around 20 tons, leading to higher payload capacity [20].…”

Section: Large Boosters and Main Stagesmentioning

confidence: 99%

“…Evidently, in-space applications, such as GTO/GEO and longer orbital transfer manoeuvres where a low regression rate could be beneficial [33][34][35][36], have been evaluated as well. Lengellé et al [35] found that, the mass savings are between 3 to 4 kg when changing from a hydrazine mono-propellant system to an H 2 O 2 /PE hybrid for a small satellite (total mass 100 kg), which is significant considering that the payload mass is only 15 kg. Furthermore, for a Mars aero-capture manoeuvrer, the hybrid propulsion option would be an alternative to the hydrazine mono-propellant [37].…”

Section: In-space Propulsionmentioning

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: Large Boosters and Main Stagesmentioning

confidence: 99%

Section: In-space Propulsionmentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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“…For these reasons, they have been proposed for several applications [2][3][4][5][6][7][8][9][10][11][12][13][14][15][16], including but not restricted to upper stages and satellites/spacecrafts, which are the specific subject of this paper. Reference [2] is a review of hybrid rocket status and several potential proposed applications of this technology written in the sixties, while [3] is a similar update version done recently that describes the major challenges in hybrid hockets and future applications of hybrid-propulsion systems, including the recent market of space tourism.…”

Section: Introductionmentioning

confidence: 99%

“…References [9,10] suggest two different hybrid architectures for the upper stages of small launch vehicles. Reference [11] describes a hybrid propulsion system for orbit raising applications while reference [12] proposes the use of hybrid propulsion to lower the orbit of a small satellite launched as a secondary payload from GTO [Geostationary Transfer Orbit] to LEO [Low Earth Orbit]. References [13,14] consider a hybrid motor for a small recoverable satellite.…”

Section: Introductionmentioning

confidence: 99%

“…An example of such a situation is presented in [11] where a large hybrid is designed for orbit raising. Another example of the use of a hybrid is described in [12] where a small motor is operated cumulatively for less than 90 s to perform several maneuvers to transfer a secondary small satellite from a GTO to LEO orbit. A detailed trajectory analysis is missing so it is not known if the same set of maneuvers could be performed by a smaller (liquid) thruster operating for longer periods.…”

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confidence: 99%

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Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages

Barato

2021

Aerospace

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Ablative-cooled hybrid rockets could potentially combine a similar versatility of a liquid propulsion system with a much simplified architecture. These characteristics make this kind of propulsion attractive, among others, for applications such as satellites and upper stages. In this paper, the use of hybrid rockets for those situations is reviewed. It is shown that, for a competitive implementation, several challenges need to be addressed, which are not the general ones often discussed in the hybrid literature. In particular, the optimal thrust to burning time ratio, which is often relatively low in liquid engines, has a deep impact on the grain geometry, that, in turn, must comply some constrains. The regression rate sometime needs to be tailored in order to avoid unreasonable grain shapes, with the consequence that the dimensional trends start to follow some sort of counter-intuitive behavior. The length to diameter ratio of the hybrid combustion chamber imposes some packaging issues in order to compact the whole propulsion system. Finally, the heat soak-back during long off phases between multiple burns could compromise the integrity of the case and of the solid fuel. Therefore, if the advantages of hybrid propulsion are to be exploited, the aspects mentioned in this paper shall be carefully considered and properly faced.

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