A Novel Concept for Stratospheric Communications ... - Team-Logic

VI. ConclusionThe StarLight hybrid LTA vehicle can provide continuous communications and surveillance capabilities at70,000 to 100,000 feet at a significantly lower total cost than comparable space-based platforms. The concept isunique from other high altitude LTA vehicles because it utilizes a two stage design where the upper stage is a liftingbody. This two stage design provides a number of performance benefits including: separating the solar cells from theenvelope hull and payload modularity. Also, the upper stage envelope is a low cost disposable balloon, while thelower stage is recovered. The lifting body shape of the upper stage allows the system to fly above the neutralbuoyancy point during wind gusts and dash back to the target area after the wind gusts have subsided. The systemdesign is also unique because a great majority of the materials are commercial-off-the-shelf, thereby reducingdevelopment time and costs. The development of the StarLight has been advanced significantly recently throughenvelope material selection as well as detailed thermal, aerodynamic, trajectory, and sizing analysis.AcknowledgmentsThe authors thank Dr. Hugh Thornburg of MSRC at Wright-Patterson AFB AFRL for all of his supportconducting the CFD analysis during the past year.References1 Scott, W. B., “Novel hybrid near-space platform awaits a visionary financial angel,” Aviation Weekly and SpaceTechnology, Page 60, January 30, 2006.2 Cadogan, D.P. Smith, T., Lee, R., Scarborough, S.E., Graziosi, D. “Inflatable and Rigidizable Wing Components forUnmanned Aerial Vehicles,” AIAA-2003-1801, 44th AIAA/ASME/ ASCE/AHS/ASC Structures, Structural Dynamics, andMaterials Conference and Exhibit AIAA Gossamer Spacecraft Forum, Norfolk, VA, April 7-10, 2003.3 Simpson, A. Santhanakrishnan, J. Jacob, S. Smith, J. Lumpp, D. Cadogan, M. Mackusick, S. Scarborough, “Flying on Air:UAV Flight Testing with Inflatable Wing Technology”, AIAA-2004-6570 AIAA 3rd "Unmanned Unlimited" TechnicalConference, Workshop and Exhibit, Chicago, Illinois, Sep. 20-23, 2004.4 Rowe, J.M., Smith, S.W., Simpson, A., Jacob, J., Scarborough, S.E., “Development of a Finite Element Model of WarpingInflatable Wings ,” AIAA-2006-1697, 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and MaterialsConference, Newport, Rhode Island, May 1-4, 2006.5 Smith, S.W., Jacob, J., Jones, R.J., Scarborough, S.E., Cadogan, D.P., “A High-Altitude Test of Inflatable Wings for Low-Density Flight Applications,” AIAA-2006-1696, 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics andMaterials Conference, Newport, Rhode Island, May 1-4, 2006.6 Cadogan, D.P., Scarborough, S.E., Gleeson, D., Dixit, A, Jacob, J., Simpson, A. “Recent Development and Test of InflatableWings,” AIAA-2006-2139, 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference,Newport, Rhode Island, May 1-4, 2006.7 Pankine, Alexey A., Heun, Matthew K., Nguyen, Nam and Schlaifer, R. Stephen. “NAVAJO: Advanced Software Tool forBalloon Performance Simulation,” AIAA 2005-7411, AIAA 5 th Aviation, Technology, Integration, and Operations Conference(ATIO), Arlington, VA, September 26-28, 2005.8 Miller, T., and Mandel, M. “Airship Envelopes: Requirements, Materials, and Test Methods,” ILC Dover Publication, 2002.9 Welch, J.V., Wang, S., Blandino, J. R., McEvoy, K., “Super Pressure Balloon Non-Linear Structural Analysis andCorrelation using Photogrammetric Analysis,” AIAA-2005-7447, AIAA 5th Aviation, Technology, Integration, and OperationsConference(ATIO) 16th Lighter-Than-Air Systems Technology Conference and Balloon Systems Conference, Arlington, VA,September 26-28, 2005.14American Institute of Aeronautics and Astronautics