The battery charger for the atmosphere Explorer B spacecraft
Battery charger for Atmosphere Explorer B spacecraft - packaging in aluminum frame rectangular configuration with three separate compartments
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Battery charger for Atmosphere Explorer B spacecraft - packaging in aluminum frame rectangular configuration with three separate compartments
A battery model is developed based on time averaging the current or power, and is shown to be an effective means of predicting the performance of a lead acid battery. The effectiveness of this battery model was tested on battery discharge profiles expected during the operation of an electric vehicle following the various SAE J227a driving schedules. The averaging model predicts the performance of a battery that is periodically charged (regenerated) if the regeneration energy is assumed to be converted to retrievable electrochemical energy on a one-to-one basis.
High temperature battery development - zeolites, anode and cathode couples, and molten salts
Radiation effects on silver and zinc battery electrodes
Three-day battery capable of operation at temperature of 425 degrees C for use on lunar and planetary probes
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Explore the source record for details and available documents.
Polymer separator materials for heat sterilizable battery
Automatic battery formation cycler and controller to determine charge capacity and to perform charge-discharge operations for electrochemical cells intended for satellite power sources
Radiation effects on silver-zinc battery electrodes
Fabrication and testing of battery separator material of modified polyethylene film
Gamma radiation effects on silver and zinc battery electrodes
Develop battery that will meet DS-2 power requirements under specified operational, environmental, and life requirements.
Development of sealed lead-acid battery with lead- calcium grid for space application
Aqueous and nonqueous electrolytic actions, and energy density measurements for dry tape battery
The Jet Propulsion Laboratory will test a lithium battery (Li- TiS2) in orbit and examine the battery after it is returned to Earth. The results will be used to suggest design changes for a battery that may eventually be 3-4 times lighter than the equivalent NiCd battery.
The Long Life (Lithium Ion) Battery is designed to replace the current Extravehicular Mobility Unit Silver/Zinc Increased Capacity Battery, which is used to provide power to the Primary Life Support Subsystem during Extravehicular Activities. The Charger is designed to charge, discharge, and condition the battery either in a charger-strapped configuration or in a suit-mounted configuration. This paper will provide an overview of the capabilities and systems engineering development approach for both the battery and the charger
Inorganic separator for high temperature silver-zinc battery