Search NASA⌕ Search

SEARCH · Search NASA

Results for “battery lifetime”

Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1983

Long life communication satellites: Electric power supply during the eclipse period

The electric batteries, essentially nickel-cadmium for French satellites such as D1 A, D1 C, D1 D, D2 B, D5 A, D5 B, etc. and the batteries for such satellites as Symphonie, ANS, INTASAT, ESRO 4, and COS-B are discussed. The experience obtained led to the development of long lifetime batteries for communication satellites. Real simulation tests showed a lifetime of four years and accelerated lifetime tests of twelve years. These batteries will be applied in OTS, METEOSAT, and Marots. At the same time, new batteries are being developed, based on nickel-hydrogen or on silver-hydrogen, which should provide longer lifetime and better reliability.

Font, S.↗
NASA NTRS1975

Microelectronic bioinstrumentation systems

The possibility of using RF fields to power biologically implanted transmitters used in biomedical experiments was investigated. This approach would be especially useful when animal subjects are strapped in chairs or confined in cages. A telemetry system using an external source of energy has the additional advantage of not being limited in operation by battery lifetime and can therefore operate for virtually infinite lengths of time. A description of a system based on this principle is given. Progress in the development of battery-driven transmitters is also reported, including an ingestible temperature telemetry system and a resistance-to-pulse frequency convertor for implantable temperature telemetry systems.

Ko, W. H.↗
NASA NTRS1981

Battery failure model derived from flaw theory

A previously derived failure model for battery lifetime is discussed in terms of growth rate of the flaw, distribution of flaw sizes, and number of flaws. Equations are presented for determining the failure model for a nickel cadmium battery.

Schulman, I.↗
NASA NTRS1969

Ionene membrane battery separator

Ionic transport characteristics of ionenes, insoluble membranes from soluble polyelectrolyte compositions, are studied for possible application in a battery separator. Effectiveness of the thin film of separator membrane essentially determines battery lifetime.

Moacanin, J.↗
NASA NTRS1990

Preliminary results from the advanced photovoltaic experiment flight test

The Advanced Photovoltaic Experiment is a space flight test designed to provide reference cell standards for photovoltaic measurement as well as to investigate the solar spectrum and the effect of the space environment on solar cells. After a flight of 69 months in low earth orbit as part of the Long Duration Exposure Facility set of experiments, it was retrieved in January, 1990. The electronic data acquisition system functioned as designed, measuring and recording cell performance data over the first 358 days of flight; limited by battery lifetime. Significant physical changes are also readily apparent, including erosion of front surface paint, micrometeoroid and debris catering and contamination.

Brinker, David J.↗
NASA NTRS1990

Preliminary flight test results from the advanced photovoltaic experiment

The Advanced Photovoltaic Experiment is a space flight test designed to provide reference cell standards for photovoltaic measurement as well as to investigate the solar spectrum and the effect of the space environment on solar cells. After a flight of 69 months in low earth orbit as part of the Long Duration Exposure Facility set of experiments, it was retrieved in January, 1990. The electronic data acquisition system functioned as designed, measuring and recording cell performance data over the first 358 days of flight, limited by battery lifetime. Significant physical changes are also readily apparent, including erosion of front surface paint, micrometeoroid and debris catering and contamination.

Brinker, David J.↗
NASA NTRS1990

Preliminary results from the Advanced Photovoltaic Experiment flight test

The Advanced Phototovoltaic Experiment is a space flight test designed to provide reference cell standards for photovoltaic measurements and to investigate the solar spectrum and the effect of the space environment on solar cells. After a flight of 69 months in low earth orbit as part of the Long Duration Exposure Facility set of experiments, it was retrieved in January 1990. The electronic data acquisition system functioned as designed, measuring and recording cell performance data over the first 358 days of flight, limited by battery lifetime. Significant physical changes are also readily apparent, including erosion of front surface paint, micrometeoroid and debris cratering, and contamination.

Brinker, David J.↗
NASA NTRS1993

INMARSAT's personal communicator system

Inmarsat has been providing near global mobile satellite communications since 1982 and Inmarsat terminals are currently being used in more than 130 countries. The terminals have been reduced in size and cost over the years and new technology has enabled the recent introduction of briefcase sized personal telephony terminals (Inmarsat-M). This trend continues and we are likely to see Inmarsat handheld terminals by the end of the decade. These terminals are called Inmarsat-P and this paper focuses on the various elements required to support a high quality service to handheld terminals. The main system elements are: the handheld terminals; the space segment with the associated orbits; and the gateways to terrestrial networks. It is both likely and desirable that personal handheld satellite communications will be offered by more than one system provider and this competition will ensure strong emphasis on service quality and cost of ownership. The handheld terminals also have to be attractive to a large number of potential users, and this means that the terminals must be small enough to fit in a pocket. Battery lifetime is another important consideration, and this coupled with radiation safety requirements limits the maximum radiated EIRP. The terminal G/T is mainly constrained by the gain of the omnidirectional antenna and the noise figure of the RF front end (including input losses). Inmarsat has examined, with the support of industry, a number of Geosynchronous (GSO), Medium Earth Orbit (MEO) and Low Earth Orbit (LEO) satellite options for the provision of a handheld mobile satellite service. This paper describes the key satellite and orbit parameters and tradeoffs which affect the overall quality of service and the space segment costing. The paper also stresses not only the importance of using and sharing the available mobile frequency band allocations efficiently, but also the key considerations affecting the choice of feeder link bands. The design of the gateways and the terrestrial network is critical to the overall viability of the service, and this paper also examines the key technical parameters associated with the Land Earth Stations (LES), which act as gateways into the Public Switched Telephone Network (PSTN). These not only include the design tradeoffs associated with the LES, but also the different terrestrial network interface options. The paper concludes with a brief description of the satellite propagation conditions associated with the use of handheld terminals. It describes how the handheld results in a number of propagation impairments which are not common to the previous measurements associated with vehicle mounted antennas. These measurements indicate that there is a complex tradeoff between link margin and the elevation angle to the satellite which has a significant impact on the space segment requirements and costing.

Hart, Nick↗
NASA NTRS2005

STS-114: Discovery Day 3/Mission Status Briefing

Paul Hill, STS-114 Lead Flight Director, and John Shannon, Flight Operations and Integrations Manager for the Space Shuttle Program were present. Paul gave a detailed description of the Orbiter's performance upon its arrival on the International Space Station, orbital rendezvous and docking was completed, performance was nominal by all measures, and crew is already inside the ISS. He also briefly mentioned the next day crew activities, robotics work and first space walk. John emphasized on ground technical engineering tasks, data gathering and inspection of data, imagery and damage assessment, assessing the performance of the external tank, engineering analysis, and the increase of understanding of the overall condition of the vehicle. Safety of the vehicle, battery lifetime, foam loss, tile damage, post launch analysis were some of the topics discussed with the News Media.

Source record↗
NASA NTRS2005

STS-114: Discovery Day 3 Mission Status Briefing

Paul Hill, STS-114 Lead Shuttle Flight Director and John Shannon, Space Shuttle Flight Operations and Integration Manager are seen in this STS-114 flight day three Mission Status Briefing. Hill expresses that the Discovery Orbiter is performing beautifully and that STS-114 crew performed a picture perfect rendezvous. He also shows a video of the Rendezvous Pitch Maneuver (RPM) where Commander Eileen Collins slowly flips Discovery in a circle to give the Expedition 11 crew a view of Discovery's heat resistant tiles. He talks about the removal of the Multi-Purpose Logistics Module (MPLM) from Discovery's payload bay using the ISS Robotic Arm. Shannon discusses two objectives that his team is fulfilling on this mission. They include: 1) Understanding the health of Space Shuttle Discovery; and 2) Assessing the performance of the External Tank. Questions from the news media pertaining to the life expectancy of the Space Shuttle Discovery, battery lifetime on the wing leading edge impact sensors, foam loss, PAL ramps, and the safety of the Space Shuttle Discovery are addressed.

Source record↗
NASA NTRS2010

Distributed Impact Detector System (DIDS) Health Monitoring System Evaluation

Damage due to impacts from micrometeoroids and orbital debris is one of the most significant on-orbit hazards for spacecraft. Impacts to thermal protection systems must be detected and the damage evaluated to determine if repairs are needed to allow safe re-entry. To address this issue for the International Space Station Program, Langley Research Center and Johnson Space Center technologists have been working to develop and implement advanced methods for detecting impacts and resultant leaks. LaRC funded a Small Business Innovative Research contract to Invocon, Inc. to develop special wireless sensor systems that are compact, light weight, and have long battery lifetimes to enable applications to long duration space structures. These sensor systems are known as distributed impact detection systems (DIDS). In an assessment, the NASA Engineering and Safety Center procured two prototype DIDS sensor units to evaluate their capabilities in laboratory testing and field testing in an ISS Node 1 structural test article. This document contains the findings of the assessment.

Prosser, William H.↗
NASA NTRS1972

Lifetime estimates for sterilizable silver-zinc battery separators

The lifetime of separator membranes currently employed in the electrolyte environment of silver-zinc batteries was estimated at 3 to 5 years. The separator membranes are crosslinked polyethylene film containing grafted poly (potassium acrylate)(PKA), the latter being the hydrophilic agent which promotes electrolyte ion transport. The lifetime was estimated by monitoring the rate of loss of PKA from the separators, caused by chemical attack of the electrolyte, and relating this loss rate to a known relationship between battery performance and PKA concentration in the separators.

Cuddihy, E. F.↗
NASA NTRS2023

An Accelerated Life Testing Dataset for Lithium-Ion Batteries With Constant and Variable Loading Conditions

The dataset repository is organized into three main folders, each containing one group of life cycled battery packs. Within each folder individual battery packs own their dedicated csv file for continuous data logging, which are named with their respective battery pack number. The folders are named: - regular_alt_batteries: Containing one csv file for each battery pack cycled at the same load level or load range throughout lifetime - recommissioned_batteries: Containing one csv file for each battery pack cycled at different load levels at varying life stages - second_life_batteries: Containing one csv file for each second life battery pack cycled at constant current througout the second life

Li-ion Battery↗
NASA NTRS1978

Photovoltaic power-system options for the manned space construction base

The function of the proposed manned Space Construction Base (SCB) is to provide a permanent manned orbital facility for the construction and operation of a variety of space experiments, ranging from a space-processing development to on-orbit-constructed microwave radiometers and antennas. A typical SCB system might reach initial operational capability in low earth orbit in 1985, have a 10-year mission duration, and have an initial power requirement of 50 kWe. A summary of the requirements imposed by the SCB on the electrical power system (EPS) is presented in a table. Attention is given to EPS options, baseline power platform system operations, an energy storage system evaluation, advanced-technology NiCd batteries and lifetime, and orbital buildup operations.

Mckhann, G. G.↗
NASA NTRS1991

Effect of sinter fracture and ohmic resistance on capacity retention in the nickel oxide electrode

The lifetime of batteries which utilize the nickel oxide electrode is often limited because this electrode loses a significant portion of its capacity as it is cycled. It is asserted that this capacity loss may often be attributed to cracking or separation of the conductive nickel sinter in the electrode, which forces electronic current to pass through the poorly conducting hydrated oxide and thus imposes a significant ohmic resistance. The model indicates that the oxide develops a nearly insulating layer which prevents complete discharge in the cycled electrode at usable rates. The capacity retention can be improved by reducing the cyclic stresses or strengthening the current collecting structure, redistributing it to provide a shorter current path through the solid phase, or by increasing the conductivity of the oxide to delay the formation of an insulating layer.

Lanzi, Oscar↗
NASA NTRS1983

Ni-H2 batteries for communications satellites

Ni-H2 batteries are just now being put into service. All of the remaining INTELSAT V satellites (approximately 10), starting with the next to be launched in early 1983, will use Ni-H2 batteries. In addition, the next generation of INTELSAT VI satellites, and probably INTELSAT VII and VIII, will use Ni-H2 batteries. This means that international telecommunications satellites will use Ni-H2 batteries through the 1990's. It is projected that the lifetime of these batteries will be greater than 10 years at deep depth-of-discharge (DOD), and that the battery subsystem will no longer limit satellite lifetime or communications capability during eclipse periods. This paper discusses the advantages of the Ni-H2 battery, as compared with the Ni-Cd battery, for telecommunications satellites.

Dunlop, J. D.↗