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Table 34: Pelican Technical SpecificationsFigure 52: Pelican Envelope Profiles 52Length: 256 ft.Diameter: 96 ft. (max)Volume: 732,110 cu. ft.Max Payload: 44,000 lbs.Payload Type: Airlift/logistics cargoRange: Hangar Demo OnlyFlight Ceiling: Hangar Demo OnlyDuration: Hangar Demo OnlyCruise Speed: Hangar Demo OnlyMax Speed: Hangar Demo OnlyPayload Power Available: 18–19 kWMass: 41,117 lbs.utilized in the Pelican airship. The BAAVprogram, which was completed in 2009,conducted hangar tests to prove a compositerigid structure application to a LTAvehicle. 51Project Pelican is an effort led by theASD(R&E)-RRTO and managed inconjunction with the NASA Ames ResearchCenter. The effort seeks to combine avariety of previously tested technologiesinto a single, non-deployable technologydemonstrator. Contractor Aeros Corporationleads the development and integration work.Aeros was awarded the contract for theeffort in May of 2009. ASD(R&E)-RRTOhas responsibility for the overall projectrequirements and provides funding withinDoD and Congressional guidance. NASAAmes Research Center is responsible foradministering the contract and providingtechnical oversight. Additional program andtechnical support is provided by AirForce/AFRL. 51Pelican is currently in the subsystemverification and vehicle integration phase.Preparations are also being made for thehangar demonstration, which is currentlyscheduled for late 2012. The hangardemonstration has several objectives. Thefirst goal is to demonstrate the effectivenessof the variable buoyancy control COSHsystem that changes the density of thevehicle’s helium to affect control over theairship’s buoyancy. The second goal is toprove the rigid lightweight-compositeexternal structure of the RAVB aircraftmaintains envelope integrity without relyingon differential gas pressure.56
Figure 53: Illustration Showing Lightweight Rigid Structure and HPE 53Another goal is to demonstrate the airshipdoes not need external ballasts tocompensate for offloading payloads.Additional tests will demonstrate VTOL,forward/aft motion, and ground handling.The contract is set to end after the hangardemonstration. 51Pelican was initiated in FY08 with fundingfrom OSD. This proof of concept projectwas planned for a five-year period from lateFY08 to FY13. Current plans are tocomplete a hanger demonstration, with nointent to provide additional funding beyondthat point. 5157
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SUMMARY REPORT OF DoD FUNDED LIGHTE
Page 3 and 4:
TABLE OF CONTENTSEXECUTIVE SUMMARY
Page 5 and 6:
Figure 11: Computer Rendering of Al
Page 7 and 8:
Table 22: HALE-D Program Overview .
Page 9 and 10:
EXECUTIVE SUMMARYIn the Senate repo
Page 11 and 12:
for unmanned aerial vehicle and cru
Page 13 and 14:
Integrated Sensor Is Structure (ISI
Page 15 and 16:
PREFACECongress, through the Senate
Page 17 and 18:
PURPOSEThe purpose of this document
Page 19 and 20: INTRODUCTIONBackgroundModern LTA cr
Page 21 and 22: ground, large aerostats are anchore
Page 23 and 24: AirliftAirships, particularly hybri
Page 25 and 26: AEROSTAT PROGRAMSAerostats are air
Page 27 and 28: Aerostat Test Bed (ATB)Table 2: ATB
Page 29 and 30: AltusTable 4: Altus Program Overvie
Page 31 and 32: would otherwise lack organic survei
Page 33 and 34: Table 7: JLENS Technical Specificat
Page 35 and 36: Persistent Ground Surveillance Syst
Page 37 and 38: and advance systems capabilities as
Page 39 and 40: Length: 117 ft.Width: 39 ft.Height:
Page 41 and 42: Rapid Aerostat Initial Deployment (
Page 43 and 44: Rapidly Elevated Aerostat Platforms
Page 45 and 46: tether lengths to support different
Page 47 and 48: Length: 26.87 ft.Table 17: STMPAS T
Page 49 and 50: Table 19: TARS Technical Specificat
Page 51 and 52: AIRSHIP PROGRAMSDespite the fact th
Page 53 and 54: Figure 30: Size Comparison for Hybr
Page 55 and 56: Table 21: Blue Devil 2 Technical Sp
Page 57 and 58: High-Altitude Long Endurance-Demons
Page 59 and 60: HiSentinelTable 24: HiSentinel Prog
Page 61 and 62: Table 26: Comparison of HiSentinel
Page 63 and 64: Table 28: ISIS Technical Specificat
Page 65 and 66: Table 30: LEMV Technical Specificat
Page 67 and 68: MZ-3AVehicle Class: Conventional Ai
Page 69: PelicanTable 33: Pelican Program Ov
Page 73 and 74: Table 36: Skybus Technical Specific
Page 75 and 76: APPENDICESAppendix A- BalloonsIntro
Page 77 and 78: could be separated from the balloon
Page 79 and 80: Appendix B - Glossary of TermsAAero
Page 81 and 82: ATECAVAWSSBBAAVBCTBLOSCC2C3IC4ISRC5
Page 83 and 84: IFFIPTISRITSJJCTDJIEDDOJMUAJROCJUON
Page 85 and 86: SIGINTSINCGARSSIPRNetSMDBLSMDCSRVSu
Page 87 and 88: Appendix D - References1. The Senat
Page 89 and 90: 43. “Lockheed Martin ISIS”. HIS
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