SBIR-STTR Award

New Structures for Large Sensor Array Platforms
Award last edited on: 3/22/2004

Sponsored Program
SBIR
Awarding Agency
NASA : JPL
Total Award Amount
$650,000
Award Phase
2
Solicitation Topic Code
-----

Principal Investigator
Dave Murphy

Company Information

ATK-Able Engineering Company Inc (AKA: ABLE~AEC-ABLE Engineering Company Inc)

600 Pine Avenue
Goleta, CA 93117
   (805) 685-2262
   dave.messner@atk.com
   www.aec-able.com
Location: Single
Congr. District: 24
County: Santa Barbara

Phase I

Contract Number: ----------
Start Date: ----    Completed: ----
Phase I year
2003
Phase I Amount
$75,000
The success of SRTM (Shuttle Radar Topography Mission) illustrates the utility of radar interferometry from space. The intent of the proposed work is to develop system capability to deploy a one-kilometer baseline radar interferometer launched in a single mission from a standard launch vehicle. This system is enabled by on a novel deployable structure technology. This structural approach has the potential of increasing stowed packaging efficiency by a factor of >2x and decreasing linear mass density by a factor of >8x better than SRTM while maintaining equivalent strength, stability, and stiffness. The challenge of this technology is to develop methods of utilizing high modulus, low CTE (coefficient of thermal expansion) graphite fiber composites in an arrangement that does not exceed the strain limits of the material when stowed yet retains the desired stiffness and thermal stability when deployed. The approach is to add an additional order of structural hierarchy to the overall system by further optimizing the constituent columns of the truss into simple deployable truss structures themselves. Each column is comprised of a set of mutually stabilized rods that can be configured by varying the number and size of rods and stabilizers for required axial stiffness and buckling strength. POTENTIAL COMMERCIAL APPLICATIONS Once sufficiently characterized, the proposed technology is envisioned to have broad applicability for any mission requiring the capability to deploy stiff, stable and extremely mass and volume efficient structures. The technology is directly applicable to sensor array structural platforms. The ability to rapidly configure large, single-mission structures will have commercialization opportunities for a wide variety of communication and imaging spacecraft. Also, economic barriers common to small payloads associated with the cost of specialty-run composites will be reduced due to the generalized nature of the construction of the proposed structure, which should also prove a benefit to the general scientific community.

Phase II

Contract Number: ----------
Start Date: ----    Completed: ----
Phase II year
2004
Phase II Amount
$575,000
___(NOTE: Note: no official Abstract exists of this Phase II projects. Abstract is modified by idi from relevant Phase I data. The specific Phase II work statement and objectives may differ)___ The success of SRTM (Shuttle Radar Topography Mission) illustrates the utility of radar interferometry from space. The intent of the proposed work is to develop system capability to deploy a one-kilometer baseline radar interferometer launched in a single mission from a standard launch vehicle. This system is enabled by on a novel deployable structure technology. This structural approach has the potential of increasing stowed packaging efficiency by a factor of >2x and decreasing linear mass density by a factor of >8x better than SRTM while maintaining equivalent strength, stability, and stiffness. The challenge of this technology is to develop methods of utilizing high modulus, low CTE (coefficient of thermal expansion) graphite fiber composites in an arrangement that does not exceed the strain limits of the material when stowed yet retains the desired stiffness and thermal stability when deployed. The approach is to add an additional order of structural hierarchy to the overall system by further optimizing the constituent columns of the truss into simple deployable truss structures themselves. Each column is comprised of a set of mutually stabilized rods that can be configured by varying the number and size of rods and stabilizers for required axial stiffness and buckling strength. POTENTIAL COMMERCIAL APPLICATIONS Once sufficiently characterized, the proposed technology is envisioned to have broad applicability for any mission requiring the capability to deploy stiff, stable and extremely mass and volume efficient structures. The technology is directly applicable to sensor array structural platforms. The ability to rapidly configure large, single-mission structures will have commercialization opportunities for a wide variety of communication and imaging spacecraft. Also, economic barriers common to small payloads associated with the cost of specialty-run composites will be reduced due to the generalized nature of the construction of the proposed structure, which should also prove a benefit to the general scientific community.