Terra flexible blanket solar array deployment, on-orbit performance and future applications

Kurland, R.M.; Schurig, H.; Rosenfeld, M.; Herriage, M.J.; Gaddy, Edward M.; Keys, Denney; Faust, C.D.; Andiario, William; Kurtz, Michael J.; Moyer, E. L.

doi:10.1109/pvsc.2000.916070

Cited by 6 publications

(2 citation statements)

References 5 publications

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“…The Terra satellite, recorded in the transits, is known to possess a large solar array area of 45 m 2 rotating on one axis to always face the sun [4]. Given the 582.7-mm focal length of the experimental system, each square image pixel subtends 7:2 10 4 deg along the edge.…”

Section: Experimental Measurement Of Satellite-occluding Areamentioning

confidence: 99%

Photometric Detection of Known Sun-Occluding Satellites

Poller

Culp

2009

Journal of Spacecraft and Rockets

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Section: Experimental Measurement Of Satellite-occluding Areamentioning

confidence: 99%

Photometric Detection of Known Sun-Occluding Satellites

Poller

Culp

2009

Journal of Spacecraft and Rockets

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“…120-V was selected to match operating high-voltage power systems on NASA spacecraft, i.e. the International Space Station (ISS) EPS secondary bus and the Terra spacecraft primary bus (Kurland et al, 2000). 300-V was selected since this is the lowest practical voltage to directly operate a HET without upconversion.…”

Section: Pmad Architecturementioning

confidence: 99%

Effect of Voltage Level on Power System Design for Solar Electric Propulsion Missions

Kerslake

2004

Journal of Solar Energy Engineering

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This paper presents study results quantifying the benefits of higher voltage, electric power system designs for a typical solar electric propulsion spacecraft Earth orbiting mission. A conceptual power system architecture was defined and design points were generated for several system voltages using state-of-the-art or advanced technologies. A 300-V “direct-drive” architecture was also analyzed to assess the benefits of directly powering the electric thruster from the photovoltaic array without up-conversion. Computational models were exercised to predict the performance and size power system components to meet spacecraft mission requirements. Pertinent space environments were calculated for the mission trajectory and an electron current collection model was developed to estimate photovoltaic array losses due to natural and induced plasma environments. The secondary benefits of power system mass savings for spacecraft propulsion and attitude control systems were also quantified. Results indicate that considerable spacecraft wet mass savings were achieved by the 300-V and 300-V direct-drive architectures.

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