Showing papers on "Photovoltaic system published in 1968"

Self-Adapting dc Converter for Solar Spacecraft Power Supply Selbstanpassender Gleichstromwandler für die Energieversorgung eines Sonnensatelliten

Abstract: The voltage-current characteristic of solar cells that provide power for a spacecraft can vary over a wide range. For maximum power transfer from the solar cells to the battery system a power converter has to be designed that adjusts its input impedance to a value equal to the output impedance determined by the operating power characteristic of the solar cells. This paper discusses a circuit and calculations for a design to match this condition. The proposed power converter is simple, lightweight, and reliable and will be used in the Sunblazer satellite.

2 to 10 kilowatt solar or radioisotope Brayton power system.

Abstract: Solar or radioisotope Brayton power system efficiencies estimated for ground test configurations

Use of unilluminated solar cells as shunt diodes for a solar array

Abstract: In a plurality of solar cells connected in a number of series paths to form both shaded and illuminated solar batteries, each individual cell of a shaded battery being electrically connected in parallel but in opposite polarity with a corresponding cell of an illuminated solar battery, the p-n junction solar cell of the shaded battery behaving as a forward biased diode forming a by-pass conducting path around the corresponding illuminated cell should it become non-conductive to thereby achieve an uninterrupted generation of electrical current by the remaining illuminated cells of the solar battery containing the non-conducting cell.

Electronic charge monitor

Abstract: The charging current supplied by a satellite solar cell array is monitored to produce a voltage signal proportional to the charging current. This voltage signal is then applied to a finite time integrator circuit whose output is, in turn, applied to a level detector. The level detector functions to clear the integrator circuit and generate an output pulse each time the integrated signal indicates that a predetermined amount of electrical charge has been supplied to the satellite battery by the solar array. The output pulses from the level detector circuit are first scaled down so that the satellite''s telemetry system handles no more data than is necessary to indicate accurately the status of the satellite''s power system and these scaled-down pulses are then interfaced into the satellite''s telemetry system for transmission to a remote receiving station.

Solar cell performance at Jupiter temperature and solar intensity.

Abstract: Photovoltaic properties of CdS thin film solar cells and silicon cells at Jupiter temperature and solar intensity

The ion engine and large solar array for the x5 spacecraft.

Abstract: : A description is given of the ion engine and the 550 W deployable solar array proposed for the Black Arrow X5 spacecraft. Problem areas are discussed and an indication is given of the present state of development. (Author)

Power system design for a Jupiter solar electric propulsion spacecraft

Abstract: The design concept includes a large-area photovoltaic solar array for primary electrical power, a hibernating Ag/Zn battery subsystem for energy storage, and power conditioning equipment for conversion and distribution of power to spacecraft loads.

Status of photovoltaic power technology.

Abstract: The status of photovoltaic power technology is reviewed primarily from the viewpoint of current and future applications of the technology to the exploration and utilization of space. The photovoltaic solar cell has been the electric power workhorse throughout the first decade of the space age. The technology has shown steady improvement in reliability, increased efficiency, reduced cost, increased power per unit of hardware weight and ability to withstand extremes of the space environment. New developments are underway to increase solar cell and array size, to reduce stowage volume during boosting into orbit and to improve resistance to space radiation and thermal cycling. Silicon cell electrical contacts and interconnections, low energy proton damage to small exposed cell areas and instability of CdS thin film solar cells are examples of problems receiving attention at this time. The ongoing development of large, 2500–3000 ft2 , solar cell arrays to power the planned Apollo Applications Telescope/Workshop Cluster demonstrates the growing confidence in the ability of photovoltaic power to handle space missions of the future. As photovoltaic technology advances and economic conditions change, the solar cell may well find large scale terrestrial markets.

High-temperature annealable solar array.

Abstract: Bonded solderless solar cell panel prototype withstanding high annealing temperature and thermal shock without electrical or mechanical degradation

Pioneer's solar-cell array

Abstract: Solar array as primary electrical power source of Pioneer deep space probes, comparing performance data with test and design data

Design and performance of two vacuum chambers and solar simulators for solar-cell research

Abstract: Design and performance of two vacuum chambers and solar-radiation simulators for solar-cell research

A design concept for a 30 watts per pound rollup solar array.

Abstract: Design concept for rollup solar array configuration, discussing structural stability, power-to-weight ratio and analytical model

Gamma irradiation of lithium silicon solar cells.

Abstract: Radiation damage and recovery of lithium-diffused silicon p-n solar cells, measuring photovoltaic parameters as function of gamma radiation fluence

Large solar arrays for multi-mission lunar surface exploration.

Abstract: Solar arrays applicability in conjunction with fuel cells and batteries considered for supplying power for lunar roving vehicles