High Watts per Kilogram - Advanced Integration and Heat Management solar array technology (HaWK-AIHM ), Phase I

Metadata Updated: February 28, 2019

Small satellite architectures have become a desirable low cost alternative to larger heritage spacecraft for advanced scientific missions. Unfortunately, the traditional component make-up of a small satellite or cubesats is for short duration missions and not specifically designed for space environment resiliency. NASA has identified several scientific missions which would benefit from highly engineered, space environment tolerant and high reliability components. MMA Design (MMA) proposes new innovations in small satellite deployable solar arrays for theses missions, specifically targeting high reliability, simple and heritage proven designs, and high performance. • Composite deployable hinge mechanism - due to volumetric constraints and stowed thickness requirements, an innovative composite panel-to-panel hinge mechanism is required. MMA has extensive knowledge in the design, manufacturing and test of composite tape hinges for deployable structures. The challenges that will be addressed in this effort is how to design a composite hinge with a tight stowed radius of curvature and a method of integration to the substrate panels that provides higher thermal conductivity than a traditional clevis hinge. • Advance high stiffness, high-k solar array substrates, multi-functional - limitations with traditional polyimide or glass-fiber substrates is that they exhibit low stiffness and thermal conductivity properties. Alternatively, High-K Mesophase-pitch based graphite fibers would provide magnitudes higher thermal conductivity, thus providing better heat transfer throughout the solar array panel. Also proposed are innovations in co-cured substrate construction whereby a highly emissive film is cured directly into the substrate panel creating a surface for significant heat rejection a on the backside of the solar array. The front side of the panel will also include a cured in circuit trace, which will significantly reduce wiring routing on the solar panel.

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Public: This dataset is intended for public access and use. License: U.S. Government Work

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Dates

Metadata Created Date August 1, 2018
Metadata Updated Date February 28, 2019

Metadata Source

Harvested from NASA Data.json

Additional Metadata

Resource Type Dataset
Metadata Created Date August 1, 2018
Metadata Updated Date February 28, 2019
Publisher Space Technology Mission Directorate
Unique Identifier TECHPORT_93542
Maintainer
TECHPORT SUPPORT
Maintainer Email
Public Access Level public
Bureau Code 026:00
Metadata Context https://project-open-data.cio.gov/v1.1/schema/catalog.jsonld
Metadata Catalog ID https://data.nasa.gov/data.json
Schema Version https://project-open-data.cio.gov/v1.1/schema
Catalog Describedby https://project-open-data.cio.gov/v1.1/schema/catalog.json
Harvest Object Id 1298d771-78de-42fa-a6aa-368c20d3f8d2
Harvest Source Id 39e4ad2a-47ca-4507-8258-852babd0fd99
Harvest Source Title NASA Data.json
Data First Published 2017-12-01
Homepage URL https://techport.nasa.gov/view/93542
License http://www.usa.gov/publicdomain/label/1.0/
Data Last Modified 2018-07-19
Program Code 026:027
Source Datajson Identifier True
Source Hash 4548e8b56bd3f7bff74efa13623386c3867c8fbb
Source Schema Version 1.1

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