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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.

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At least 55 records · Page 3

Operational compatibility of 30-centimeter-diameter ion thruster with integrally regulated solar array power source

System tests were performed in which Integrally Regulated Solar Arrays (IRSA's) were used to directly power the beam and accelerator loads of a 30-cm-diameter, electron bombardment, mercury ion thruster. The remaining thruster loads were supplied from conventional power-processing circuits. This combination of IRSA's and conventional circuits formed a hybrid power processor. Thruster performance was evaluated at 3/4- and 1-A beam currents with both the IRSA-hybrid and conventional power processors and was found to be identical for both systems. Power processing is significantly more efficient with the hybrid system. System dynamics and IRSA response to thruster arcs are also examined.

Gooder, S. T.↗

Integrated Solar-Energy-Harvesting and -Storage Device

A modular, integrated, completely solid-state system designed to harvest and store solar energy is under development. Called the power tile, the hybrid device consists of a photovoltaic cell, a battery, a thermoelectric device, and a charge-control circuit that are heterogeneously integrated to maximize specific energy capacity and efficiency. Power tiles could be used in a variety of space and terrestrial environments and would be designed to function with maximum efficiency in the presence of anticipated temperatures, temperature gradients, and cycles of sunlight and shadow. Because they are modular in nature, one could use a single power tile or could construct an array of as many tiles as needed. If multiple tiles are used in an array, the distributed and redundant nature of the charge control and distribution hardware provides an extremely fault-tolerant system. The figure presents a schematic view of the device.

whitacre, Jay↗

Pathfinder Technology Demonstrator (PTD) Status

This paper will provide the status of the NASA Small Spacecraft Technology (SST) program’s Pathfinder Technology Demonstrator (PTD) series. Details on the development, launch, and operations of the recently completed PTD-1, as well as the planned operations of the upcoming PTD-3 and PTD-4 flights will be presented. Significant advances in the capabilities of nano-spacecraft over the past 15 years, coupled with improved access to space for CubeSats, have created new opportunities for scientific exploration using these high-value platforms. Continued development and demonstration of key technologies are improving the performance of the 1-unit (U) and 3U class CubeSats while expanding the reach of nano-spacecraft technologies into larger platforms, such as the 12-kilogram class “6U” buses. NASA’s PTD series is demonstrating a variety of new technologies on-orbit, providing proof of the maturity of these significant new technologies, and enhancing the performance of future CubeSats. Each of the four PTD flights consists of one 6U CubeSat weighing approximately 12 kilograms and measuring approximately 36 centimeters x 25 centimeters x 10 centimeters. Each flight is planned to characterize its payload within 90 days of insertion into low-Earth orbit. The PTD flights will demonstrate key technologies such as novel nano-spacecraft compatible propulsion systems, which enable deep space and maneuverable CubeSat flights; optical communications systems to facilitate high data rate collection and communications; and highly integrated systems that combine power and communication system elements to enable high power generation and novel integrated communication systems. The first PTD spacecraft, PTD-1, was placed in orbit by a SpaceX Falcon 9 launch in January of 2021 and demonstrated the functionality of the HYDROS propulsion system, developed by Tethers Unlimited of Bothell, Washington, over a period of six months. The PTD-3 flight, scheduled for launch in summer 2022, will demonstrate the TeraByte InfraRed Delivery, or TBIRD, optical communications payload developed by Massachusetts Institute of Technology Lincoln Laboratory in Lexington. The PTD-4 flight will demonstrate the Lightweight Integrated Solar Array and anTenna, or LISA-T, a payload that consists of an integrated solar array and transceiver developed by NASA’s Marshall Spaceflight Center in Huntsville, Alabama. The PTD spacecraft bus, integration and test, and flight operations services are provided by Tyvak Nano-Satellite Systems, Inc. (“Tyvak”) of Irvine, California. NASA’s SST program within the agency’s Space Technology Mission Directorate funds the PTD demonstration flights. The SST program rapidly develops and demonstrates capabilities for small spacecraft applicable to exploration, science, and the commercial sector. The program is based at NASA’s Ames Research Center.

Small Spacecraft↗

The sun as a star - 1982 June 14-August 13

During a 60-day period in the summer of 1982, a joint observing project between the High Altitude Observatory and the University of Hawaii was undertaken to collect a set of solar photospheric, chromospheric, and coronal data. From these data, the relationships between quantities recognized to be related to solar activity are specified. The amplitude of rotational modulation of the diagnostic parameters derived for the full disk was approximately equal to the modulation observed over an entire solar cycle. Those integrated solar data have been used as diagnostics of generalized stellar activity. A relationship between the Ca II line K flux and total inferred coronal mass of the sun existed during this observation period, and this fact leads to the hypothesis that ca II flux modulation in other stars may be used to infer stellar coronal conditions.

Fisher, R.↗

Absolute solar flux measurement shortward of 575 A

A rare-gas ionization chamber was used to obtain an accurate measurement of the absolute solar EUV flux in the 50- to 575-A region. The instrument, operating in total and near-total absorption, was flown on a solar-pointing sounding rocket on August 16, 1983. For the day of the flight, the solar activity indices were F sub 10.7 = 132.1 and R sub I = 80, and the integrated solar irradiance at the earth, corrected for atmospheric absorption, was found to be 4.31 + or - 0.31 x 10 to the 10th photons sq cm s. Almost exactly a year earlier (August 10, 1982) the same instrument measured an integrated solar flux of 5.71 + or - 0.42 x 10 to the 10th photons/sq cm s during a time of enhanced solar activity (F sub 10.7 = 209.5 and R sub I = 155).

Ogawa, H. S.↗

A solar sail integrated simulation toolkit

This paper describes an integrated set of high fidelity software tools that are being developed for the design of solar sail missions and analysis of the guidance, navigation and control (GNC) of these missions.

Lawrence, Dale↗

Lightweight, Flexible, Thin, Integrated Solar-Power Packs

Lightweight, flexible, thin, one-piece, solar-power packs are undergoing development. Each power pack of this type is a complete, modular, integrated power-supply system comprising three power subsystems that, in conventional practice, have been constructed as separate units and connected to each other by wires. These power packs are amenable to a variety of uses: For example, they could be laminated to the tops of tents and other shelters to provide or augment power for portable electronic equipment in the field, and they could be used as power sources for such small portable electronic systems as radio transceivers (including data relays and cellular telephones), laptop computers, video camcorders, and Global Positioning System receivers.

Hanson, Robert R.↗

Thin-Film Solar Arrays for Small Spacecraft

The use of thin-film based solar arrays for space applications has long been recognized as an advantageous power generation option. Thinner materials yield a mass savings, equating to lighter launch loads, larger arrays, and/or more payload allocation. Further, their mechanical flexibility lends itself well to stowage and deployment schemes, allowing for a vast improvement to both specific power (W/kg - watts per kilogram) as well as stowed power density (W/m3 - watts per cubic meter). A key application of thin-film space solar arrays is in the small satellite community; where spacecraft are largely power-starved. Their need for higher power generation coupled with the extreme mass and volume restrictions of the small spacecraft bus is driving the requirement for advanced solar arrays. And, when coupled with the relatively short operational requirements (e.g. less than 2 years) of small spacecraft, yields the perfect application for these thin-film arrays. In this presentation, NASA’s recent work on developing the Lightweight Integrated Solar Array and anTenna (LISA-T - also known as Lightweight Integrated Solar Array and Transceiver)), a thin-film solar array for small spacecraft, will be discussed. The array configuration will be shown alongside bench top deployment videos, a summary of environmental testing to date, and forward plans to a flight test. Advanced, robotic additive manufacturing of the thin-film web will also be discussed.

Carr, John A.↗

On the Angular Variation of Solar Reflectance of Snow

Spectral and integrated solar reflectance of nonhomogeneous snowpacks were derived assuming surface reflection of direct radiation and subsurface multiple scattering. For surface reflection, a bidirectional reflectance distribution function derived for an isotropic Gaussian faceted surface was considered and for subsurface multiple scattering, an approximate solution of the radiative transfer equation was studied. Solar radiation incident on the snowpack was decomposed into direct and atmospherically scattered radiation. Spectral attenuation coefficients of ozone, carbon dioxide, water vapor, aerosol and molecular scattering were included in the calculation of incident solar radiation. Illustrative numerical results were given for a case of North American winter atmospheric conditions. The calculated dependence of spectrally integrated directional reflectance (or albedo) on solar elevation was in qualitative agreement with available observations.

Chang, A. T. C.↗

On the angular variation of solar reflectance of snow

Spectral and integrated solar reflectance of nonhomogeneous snowpacks are derived assuming surface reflection of direct radiation and subsurface multiple scattering. For surface reflection, a bidirectional reflectance distribution function derived for an isotropic Gaussian faceted surface is considered, and for subsurface multiple scattering an approximate solution of the radiative transfer equation is studied. Solar radiation incident on the snowpack is decomposed into direct and atmospherically scattered radiation. Spectral attenuation coefficients of ozone, carbon dioxide, water vapor, aerosol, and molecular scattering are included in the calculation of incident solar radiation. Illustrative numerical results are given for a case of North American winter atmospheric condition. The calculated dependence of spectrally integrated directional reflectance (or albedo) on solar elevation is in qualitative agreement with available observations.

Choudhury, B. J.↗