A Low-Thrust Version of the Aldrin Cycler

Chen, K. Joseph; McConaghy, T. Troy; Okutsu, Masataka; Longuski, James M.

doi:10.2514/6.2002-4421

Cited by 12 publications

(2 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The final trajectories 23,25,26 presented in Table 2 belong to our second trajectory category where the tether sling launches a taxi vehicle to rendezvous with a vehicle in a cycler orbit. The Aldrin cycler consists of two cycler vehicles called an up-cycler and a downcycler.…”

Section: Tether Sling Performancementioning

confidence: 99%

Design of Tether Sling for Human Transportation System Between Earth and Mars

Jokic

Longuski

2004

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

Human transportation systems between Earth and Mars might benefit greatly from the construction of a tether sling facility on Phobos. A tether sling has the potential to launch vehicles from Phobos to Earth with little or no propellant expended because it is solar powered. For current trajectory designs and tether materials, we show that a tether sling facility is superior to chemical propulsion systems when multiple launches from Phobos are considered. A performance index of the ratio of tether mass to chemical-propellant mass is used to compare various mission scenarios. Ratios less than 10 are considered desirable. The most advantageous application of the tether sling occurs during a Hohmann transfer from Phobos to Earth where the mass ratio is 1.8. Next are semicyclers (ratios of 1.9 and 2.4) and a three-synodic-period cycler (8.7). Unfortunately, the Aldrin cycler does not benefit from the tether sling because the high hyperbolic velocity at Mars drives the mass ratio to infinity. For cases with desirable mass ratios, we also account for fluctuations in the cross section of the tether as a result of manufacturing uncertainties.Nomenclature A x = cross-sectional area at location x along the tether sling, m 2 F x = tensile force at location x along the tether sling, N I sp = specific impulse, s l = tether length, m m = mass, kg m p = payload mass, kg m t = tether mass, kg V ∞ = hyperbolic excess speed, m/s v = velocity, m/s v c = material characteristic velocity, m/s v * = nondimensional velocity = variation in nominal cross-sectional area V = change in velocity, m/s µ = planetary gravitational constant, m 3 /s 2 ρ = tether material density, kg/m 3 σ = tether material tensile strength, Pa

show abstract

Section: Tether Sling Performancementioning

confidence: 99%

Design of Tether Sling for Human Transportation System Between Earth and Mars

Jokic

Longuski

2004

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

“…There need to be multiple Mars cyclers ("up" and "down" versions) and they will require Earth flybys and propulsion to keep their orbit synchronization with the orbit of Earth and Mars. Analyses have shown that efficient low thrust propulsion may be sufficient for this 14 . This cycler would enable a safe, comfortable and robust exploration of Mars, along with the establishment of a Mars outpost with large scale ISRU, thus providing the means to develop Biosphere II equivalent habitats on the Mars surface.…”

mentioning

confidence: 99%

Use of Lunar Outpost for Developing Space Settlement Technologies

Purves

2008

AIAA SPACE 2008 Conference &Amp; Exposition

View full text Add to dashboard Cite

Exploration (VSE) can effectively support the development of technologies that will not only significantly enhance lunar exploration, but also enable long term crewed space missions, including space settlement. The critical technologies are: artificial gravity, radiation protection, Closed Ecological Life Support Systems (CELSS) and In-Situ Resource Utilization (ISRU). These enhance lunar exploration by extending the time an astronaut can remain on the moon and reducing the need for supplies from Earth, and they seem required for space settlement. A polar lunar outpost provides a location to perform the research and testing required to develop these technologies, as well as to determine if there are viable countermeasures that can reduce the need for Earth-surface-equivalent gravity and radiation protection on long human space missions. The types of spinning space vehicles or stations envisioned to provide artificial gravity can be implemented and tested on the lunar surface, where they can create any level of effective gravity above the ~1/6 Earth gravity that naturally exists on the lunar surface. Likewise, varying degrees of radiation protection can provide a natural radiation environment on the lunar surface less than or equal to ~1/2 that of open space at 1 AU. Lunar ISRU has the potential of providing most of the material needed for radiation protection, the centrifuge that provides artificial gravity; and the atmosphere, water and soil for a CELSS. Lunar ISRU both saves the cost of transporting these materials from Earth and helps define the requirements for ISRU on other planetary bodies. Biosphere II provides a reference point for estimating what is required for an initial habitat with a CELSS. Previous studies provide initial estimates of what would be required to provide such a lunar habitat with the gravity and radiation environment of the Earth's surface. While much preparatory work can be accomplished with existing capabilities such as the ISS, the full implementation of a lunar habitat with an Earth-like environment will require the development of a lunar mission architecture that goes beyond VSE concepts. The proven knowledge of how to build such a lunar habitat can then be applied to various approaches for space settlement.

show abstract