Innovative Structural and Material Concepts for Low-Weight Low-Drag Aircraft Design

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$124,951.00
Award Year:
2013
Program:
SBIR
Phase:
Phase I
Contract:
NNX13CL21P
Award Id:
n/a
Agency Tracking Number:
124062
Solicitation Year:
2012
Solicitation Topic Code:
A3.01
Solicitation Number:
n/a
Small Business Information
AZ, Scottsdale, AZ, 85258-4578
Hubzone Owned:
N
Minority Owned:
Y
Woman Owned:
N
Duns:
182103291
Principal Investigator:
SatyajitGhoman
Principal Investigator
(480) 945-9988
satya@zonatech.com
Business Contact:
JenniferScherr
Business Official
(480) 945-9988
jennifer@zonatech.com
Research Institute:
Stub




Abstract
The overall objective of this multi-phase project is to explore, develop, integrate, and test several innovative structural design concepts and new material possibilities that will fully leverage the expertise of the ZONA/Boeing Team for enhancing the current state-of-the-art of aircraft design. The technical objectives specific to the Phase I of this effort are threefold. First, a suitable anisotropic composite material will be identified and further studied for its suitability to the design objectives of this research. A baseline SUGAR aircraft configuration will be thoroughly studied for exploring design possibilities as well as to provide a benchmark for comparing performance improvements achieved by optimization studies performed during later stages. Secondly, the skin of the baseline SUGAR wings will then be modified to comprise of the anisotropic composite material, and the FE model will be modified to comprise of (1) distributed multiple control surfaces for AAW-type optimization in Design Route 1, and (2) variable camber continuous trailing edge flaps (VCCTEF) for control output optimization in Design Route 2. The updated FE models will then be used to further optimize the composite layup sequence as well as skin thicknesses. Thirdly, the distributed control surfaces and the VCCTEF on SUGAR high aspect ratio wing will be separately optimized for control input to achieve load alleviation and drag reduction. These two separate optimization processes of Design Route 1 and Design Route 2 will be performed iteratively to achieve an optimum low-drag low-weight design. Finally, once the optimum designs are obtained, a detailed performance review will be conducted to quantify the benefits of the non-conventional design technologies explored. A material fabrication feasibility study will also be performed.

* information listed above is at the time of submission.

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