Simple Low-Cost High-Performance Unrollable Panel Structure Solar Array for SmallSats

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9453-12-M-0061
Agency Tracking Number: F112-091-1285
Amount: $149,923.00
Phase: Phase I
Program: SBIR
Awards Year: 2012
Solicitation Year: 2011
Solicitation Topic Code: AF112-091
Solicitation Number: 2011.2
Small Business Information
75 Robin Hill Road, Building B2, Goleta, CA, -
DUNS: 825308732
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Brian Spence
 Principal Investigator
 (805) 722-8090
 Brian.Spence@DeployableSpaceSystems.com
Business Contact
 Steve White
Title: General Manager
Phone: (805) 722-4941
Email: Steve.White@DeployableSpaceSystems.com
Research Institution
 Stub
Abstract
ABSTRACT: Deployable Space Systems, Inc. (DSS) will focus the proposed SBIR program on coupling standard/advanced space-qualified high-efficiency multi-junction photovoltaics (PV) onto a simple innovative ultra-lightweight compactly-stowable elastically self-deployable panel/structure solar array system. The proposed technology, named Aladdin, will enable emerging missions and increase SmallSat operational capability. The Aladdin technology is ultra-simple and has been specifically designed to inherently provide lower risk, cost, mass, and stowage volume, allowing for dramatically increased operational capability for SmallSats. Aladdin repeatedly and elastically rolls-up in the stowed configuration occupying an ultra-compact cylindrical launch package, and then elastically deploys from its own strain/spring energy to an integrated extremely-stiff planar solar array structure. Aladdin employs high modularity and design simplicity allowing for ultra-affordability and reliability from 30W to 300W+ array/wing powers. Aladdin promises to provide revolutionary performance beyond current state-of-the-practice in terms of high specific power / lightweight (exceeding the 200 W/kg BOL AFRL goal), affordability (>30%-50% projected total cost savings depending on PV), broad modular scalability (30W to 300W+ array/wing sizes), high deployed stiffness (>1Hz deployed first mode frequency for largest wing/size), high deployed strength capability, compact stowage volume (>20-36 kW/m3 BOL), simplicity and high reliability, and operability in a 5-yr LEO or 15-yr GEO environment. BENEFIT: The proposed technology is applicable to all future DoD, NASA and commercial (including communications and earth observation) SmallSat missions as a direct replacement for existing technologies. The proposed technology promises to provide the DoD with a near-term and low-risk solar array system for SmallSat applications and will provide revolutionary performance beyond current state-of-the-practice in terms of high specific power / lightweight, affordability, broad/modular scalability, high deployed stiffness, high deployed strength, compact stowage volume, simplicity and high reliability, and operability in a 5-year LEO or 15-year GEO mission environment. The successfully developed technology will provide the end-user with mission-enabling benefits such as increased payload mass/volume capability, lower mission/spacecraft costs, and overall improved/enhanced SmallSat mission capability.

* Information listed above is at the time of submission. *

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