Solar power system options for the Radiation and Technology Demonstration spacecraft

Kerslake, Thomas W.; Haraburda, F.M.; Riehl, John P.

doi:10.1109/iecec.2000.870624

Cited by 5 publications

(3 citation statements)

References 16 publications

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“…Transient-coupled model [12], [13], obtained considering all the terms in (3). On-orbit steady-state model [3], neglecting the right hand side of (3).…”

Section: Efficiency η Modelmentioning

confidence: 99%

“…overestimate the loss of accuracy, these parameters have been fixed at the higher realistic values for SP arrays. To this end, a conventional aluminum honeycomb rigid structure has been selected, leading to a specific heat value of 945 J/KgK [16] and a unit area mass of 2,74 Kg/m 2 [12]. The coupling factors have been computed according to [16].…”

Section: Efficiency η Modelmentioning

confidence: 99%

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Solar array configurations for microsatellites flying in sunsynchronous orbits

Tancredi

D’Errico

2003 IEEE Aerospace Conference Proceedings (Cat. No.03TH8652)

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A beginning of life maximum power point, solar array power output model is developed to comparatively evaluate different kind of array configurations. To correctly describe temperature effects on power output, various thermal models are compared, selecting the better one with respect to solar panel type. Two different constanttemperature thermal models are selected in order to describe body mounted and sun pointing solar arrays. Various body mounted solar arrays configurations are compared to sun pointing ones for sunsynchronous orbits with ascending node local time ranging from 12 to 6 am. To this end, total solar array area, power time history and satellite volume are considered. Results show that configurations with one or three body mounted panels can adequately replace a sun pointing array depending on the ascending node local time.

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“…Transient-coupled model [12], [13], obtained considering all the terms in (3). On-orbit steady-state model [3], neglecting the right hand side of (3).…”

Section: Efficiency η Modelmentioning

confidence: 99%

Section: Efficiency η Modelmentioning

confidence: 99%

Solar array configurations for microsatellites flying in sunsynchronous orbits

Tancredi

D’Errico

2003 IEEE Aerospace Conference Proceedings (Cat. No.03TH8652)

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“…Most current space transportation systems, with the exception of the Deep Space 1 technology demonstration spacecraft (Kerslake et al, 2000) and the SMART-1 mission that used solar electric propulsion to go from Earth to the Moon in 10 months (Foing, 2007), depend on chemical propellants, which are composed of two components: fuels and oxidizers. Fuels and oxidizers are represented by a wide variety of chemicals, with the elements hydrogen and oxygen being common constituents (Tables 1, 2).…”

Section: Rocket Propellantsmentioning

confidence: 99%

The Significance of Lunar Water Ice and Other Mineral Resources for Rocket Propellants and Human Settlement of the Moon

Ambrose¹

Energy Resources for Human Settlement in the Solar System and Earth’s Future in Space

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F uture success in exploration and human habitation of the solar system will depend on space missions and settlements becoming more self-sustaining through exploitation of extraterrestrial (i.e., local) energy and material resources. For example, the Moon contains a wide variety of energy minerals and other resources that can potentially be used for manufacture of propellants for space transportation, volatiles for manufacture of chemicals, and metals for construction of solar power facilities, industrial plants, and structures for human habitation. If water ice in polar regions on the Moon is proven to exist in large quantities, these resources could not only support human habitation but could also be used to manufacture rocket propellants, reducing dependency on Earth for these resources, thereby making human space exploration more economically viable. Moreover, the lower gravity well of the Moon could be used as a launching site for missions to Mars and other worlds in the solar system, given the possibility of water-ice and other lunar resources. New exploration tools will need to be developed to fully and accurately characterize the potential lunar resource base. For example, detection and quantification of suspected water-ice resource in lunar polar regions in recent missions involve an array of technologies not commonly used in hydrocarbon exploration on Earth, such as synthetic aperture radar, epithermal neutron detectors, and imaging of reflected ultraviolet starlight using Lyman-alpha scattering properties. Optimal locations for potential lunar bases and industrial facilities reflect several factors that include the distribution of water ice, volatiles (nitrogen), nuclear materials (helium-3, thorium, and uranium), and metals (titanium, magnesium, and iron). Other important factors are the duration of insolation (sunlight), where solar power facilities could be constructed in polar

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