Session
Session VIII: Advanced Technologies & Subsystems, Components & Sensors II
Abstract
Spacecraft solar array systems require launch restraint hardware, array-stiffening structures to meet minimum natural frequency and provide protection during integration and test, as well as mechanisms necessary to reliably deploy the arrays. Conventional structures, mechanisms and rigid space solar cells add undue mass, cost and complexity. Current minimum solar array system costs are $1000/Watt and maximum specific power is 106 Watts/Kg at beginning of life (BOL). Mass and cost reductions are needed to meet the demanding requirements of present and future DoD, AFRL, NASA and commercial spacecraft solar arrays. New satellite programs are looking beyond state-of-the-art (SOA) power subsystems, to thin-film photovoltaics (TFPV) that are lighter and more robust than current rigid cells. Conventional approaches to TFPV array design require a separate boom, or structure to tension the array for meeting a natural frequency requirement. Tensioning a TFPV array introduces many issues with structural integrity, complexity and also significantly increases the cost and mass of the system. MSI has developed a technology innovation that extends the bounds of SOA space PV systems by eliminating conventional rigid structures and mechanisms to take full advantage of the lightweight and low volume characteristics of TFPV. This technology uses multifunctional, foldable components with stored energy to provide deployment force and deployed stiffness for meeting the demanding mass, cost and power requirements of future spacecraft programs. MSI’s TFPV enabling technology, economies of scale, non-recurring engineering, constant efficiency improvements, as well as developments in multi-junction and polyimide substrate TFPV result in a MSI PV system cost of less than $200/watt, a stowed volumetric power of greater than 90 Kw/m3, and specific power of greater than 600 watt/kg. This paper will address the characteristics of MSI’s solar array system and demonstrate the cost, mass and stowage volume benefits that will become available to satellite manufacturers in the next few years.
Self Deploying, Thin-Film PV Solar Array Structure
Spacecraft solar array systems require launch restraint hardware, array-stiffening structures to meet minimum natural frequency and provide protection during integration and test, as well as mechanisms necessary to reliably deploy the arrays. Conventional structures, mechanisms and rigid space solar cells add undue mass, cost and complexity. Current minimum solar array system costs are $1000/Watt and maximum specific power is 106 Watts/Kg at beginning of life (BOL). Mass and cost reductions are needed to meet the demanding requirements of present and future DoD, AFRL, NASA and commercial spacecraft solar arrays. New satellite programs are looking beyond state-of-the-art (SOA) power subsystems, to thin-film photovoltaics (TFPV) that are lighter and more robust than current rigid cells. Conventional approaches to TFPV array design require a separate boom, or structure to tension the array for meeting a natural frequency requirement. Tensioning a TFPV array introduces many issues with structural integrity, complexity and also significantly increases the cost and mass of the system. MSI has developed a technology innovation that extends the bounds of SOA space PV systems by eliminating conventional rigid structures and mechanisms to take full advantage of the lightweight and low volume characteristics of TFPV. This technology uses multifunctional, foldable components with stored energy to provide deployment force and deployed stiffness for meeting the demanding mass, cost and power requirements of future spacecraft programs. MSI’s TFPV enabling technology, economies of scale, non-recurring engineering, constant efficiency improvements, as well as developments in multi-junction and polyimide substrate TFPV result in a MSI PV system cost of less than $200/watt, a stowed volumetric power of greater than 90 Kw/m3, and specific power of greater than 600 watt/kg. This paper will address the characteristics of MSI’s solar array system and demonstrate the cost, mass and stowage volume benefits that will become available to satellite manufacturers in the next few years.
