Power Transmission by Laser Beam from Lunar-Synchronous Satellites to a Lunar Rover

Williams, M. D.; DeYoung, Russell J.; Schuster, G. L.; Choi, Sang H.; Dagle, Jeffery E.; Coomes, E.P.; Antoniak, Z.I.; Bamberger, Judith Ann; Bates, J.M.; Dodge, Richard E.; Wise, James A.

doi:10.4271/929437

Cited by 16 publications

(12 citation statements)

References 4 publications

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“…It is further assumed that only collimating beam microlens optics are required and that primary parabolic optics are not needed for this application. A 91.7 percent optics transmission efficiency (Williams, et al, 1993) is assumed as is a perfectly circular beam cross-sectional shape. A 12 kg/kW specific mass for laser modules plus collimating optics is assumed (Williams, et al, 1993) plus an added 10 percent mass fraction for secondary structure and mechanisms.…”

Section: Laser Subsystemmentioning

confidence: 99%

“…A 91.7 percent optics transmission efficiency (Williams, et al, 1993) is assumed as is a perfectly circular beam cross-sectional shape. A 12 kg/kW specific mass for laser modules plus collimating optics is assumed (Williams, et al, 1993) plus an added 10 percent mass fraction for secondary structure and mechanisms. A water heat pipe augmented ATCS is critically needed for coarse laser module temperature control to the baseline operating temperature of 293 K (needed for good efficiency).…”

Section: Laser Subsystemmentioning

confidence: 99%

“…The mirror radial length is a driver for optics collimation and alignment accuracy requirements that will be discussed later in this paper. The PV receiver has an assumed areal mass of 2 kg/m 2 mass (with an added 10 percent mass fraction for secondary structure and mechanisms), an optimistic conversion efficiency of 0.5 at 1368 W/m 2 and 800 nm wavelength and a 320 K control operating temperature (Williams et al, 1993). The PV receiver efficiency is scaled logarithmically with operating intensity.…”

Section: Laser Subsystemmentioning

confidence: 99%

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Lunar Surface-to-Surface Power Transfer

Kerslake

2008

AIP Conference Proceedings

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A human lunar outpost, under NASA study for construction in the 2020's, has potential requirements to transfer electric power up to 50-kW across the lunar surface from 0.1 to 10-km distances. This power would be used to operate surface payloads located remotely from the outpost and/or outpost primary power grid. This paper describes concept designs for state-of-the-art technology power transfer subsystems including AC or DC power via cables, beamed radio frequency power and beamed laser power. Power transfer subsystem mass and performance are calculated and compared for each option. A simplified qualitative assessment of option operations, hazards, costs and technology needs is also described. Based on these concept designs and performance analyses, a DC power cabling subsystem is recommended to minimize subsystem mass and to minimize mission and programmatic costs and risks. Avenues for additional power transfer subsystem studies are recommended. IntroductionConsistent with "The Vision for Space Exploration," NASA is planning to send humans to the Moon and other deep space targets. As part of the lunar exploration planning, NASA convened a "Lunar Architecture Team" or LAT. One output of the LAT was a strategy to develop a permanent human outpost at the lunar South Pole on The Shackleton Crater rim (Cooke et al., 2006). This lunar outpost will be comprised of multiple elements distributed across the lunar surface, each requiring electric power. Thus, power must be transferred from power system elements to surface elements and surface payloads. A prime example payload element is an in situ resource utilization (ISRU) oxygen production plant. Such a plant requires considerable power and must be located remotely from the outpost to minimize induced contamination from dust generation during plant operations.In support of lunar outpost power system development, the goal of this present study was to develop lunar surface-to-surface power transfer subsystem concept design options, compare option quantitative and qualitative metrics, and on the basis of this comparison, make a recommendation of the option with best balance of mass, performance, risk and cost. Most past studies on this topic have focused on a power cable power transfer approach (Gordon, 2001;Khan, et al., 2006;Sprouse, 1991). In the current study, the power transfer subsystem technology options not only include AC and DC power cables, but also radiofrequency (RF) beamed power and solid state laser module beamed power technology options. These concept designs include the required supporting equipment, such as power conditioning electronics and an Active Thermal Control System (ATCS), which can be dominant mass contributors to the total power transfer subsystem mass. The designs also incorporate the appropriate level of fault tolerance against critical and catastrophic faults required of human-rated space systems.Concept designs were prepared for power transfer levels between 1 to 50 kW and transfer distances between 0.1 to 10 km that are consisten...

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Section: Laser Subsystemmentioning

confidence: 99%

Section: Laser Subsystemmentioning

confidence: 99%

Section: Laser Subsystemmentioning

confidence: 99%

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Lunar Surface-to-Surface Power Transfer

Kerslake

2008

AIP Conference Proceedings

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“…al., where the subsystem is solar power transmitted by laser beam to a lunar rover. This literature review found four systemtype studies of interest: Eagle Engineering (1988), Williams et al (1993), Clark (1996), and Arno (1999).…”

Section: Systems Analysis Approachesmentioning

confidence: 99%

Pressurized Rover Airlocks

Cohen¹

2000

SAE Technical Paper Series

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The ability for crewmembers to explore the surface of the Moon or Mars effectively on foot remains a significant test of any exploration design.The availability of a pressurized rover would substantially increase the range of exploration by space suited crewmembers. The design of the airlock systems or functions will facilitate crewmembers in accomplishing these efforts. The pressurized rover for planetary exploration incorporates three types of airlocks or pressure ports: the EVA airlock, the sample airlock and the habitat docking port. This paper conducts a survey of selected precedents in pressurized rover design and then analyzes the key issues for airlock design.

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“…[1][2][3][4][5][6][7][8] Because laser beams are more advantageous in directionality than microwaves, high power and large-scale lasers such as free electron lasers 9) and solid lasers are under development for directed energy systems, and long-range transmission methods such as a non-diffracting single-aperture beam 10) have been proposed. However, there are several obstacles in the scaling up of a laser oscillator: In general, with the increase in power and size of a laser oscillator, it becomes expensive and difficult to oscillate in a single transverse mode to produce optimum beam collimation.…”

Section: Introductionmentioning

confidence: 99%

Energy Transmission in Space Using an Optical Phased Array

Komurasaki

Nakagawa

Ohmura

et al. 2005

Trans. JSASS Space Tech. Japan

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Main-lobe energy transmission using an optical phased array is proposed. Effects of spatial and temporal coherence of rectangular-symmetric laser arrays on energy transmission performance are evaluated in terms of the main-lobe beam quality factor and the main-lobe energy transmission efficiency. As a result, the efficiency is found to be independent of the number of laser elements and their spectral broadening, but sensitive to the aperture fill factor. The main-lobe beam quality factor remains constant for all cases.

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Power Transmission by Laser Beam from Lunar-Synchronous Satellites to a Lunar Rover

Cited by 16 publications

References 4 publications

Lunar Surface-to-Surface Power Transfer

Lunar Surface-to-Surface Power Transfer

Pressurized Rover Airlocks

Energy Transmission in Space Using an Optical Phased Array

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