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Table 32: MZ-3A Technical SpecificationsLength: 178 ft.Diameter: 43 ft.Volume: 170,000 cu. ft.Max Payload: 2,500 lbs.Figure 50: MZ-3A Specifications 49Payload type: Experimental, ISR (client driven)Flight Ceiling: 9,500 ft.Duration: >10 hours (flight), >24 hours(max endurance)Cruise Speed: 35 kts. (45 kts. max)Mass: 6,300 lbs.Payload Power: 9.5 kW (28VDC); 2.5 kW(120VAC)54
PelicanTable 33: Pelican Program OverviewFigure 51: Pelican Illustration 12Vehicle Class: Hybrid Airship Program Start: 2008Mission Set: Heavy-Lift Logistics Technology Readiness Level (TRL): 5Organization(s): ASD(R&E), NASA AmesPrimary Contractor(s): Aeros Corp.Current Status: Airship integration inprogress with plans to conduct hangar test inlate 2012PM/POC: Paul Espinosa (NASA Ames)Pelican is the consolidation of three pastefforts, and its objective is to demonstratethat the technology of scalable VTOL hasmatured and these technological advancescan be combined to create a hybrid <strong>air</strong>shipsuitable for heavy-lift operations. The goalof the program is to mitigate long-termdevelopment risks by demonstrating thefundamental characteristics of the RAVBvehicle. The key technologies to bedemonstrated include: a buoyancy controlsystem enabling ballast-independentoperations; a rigid, lightweight-compositeexternal structure; a responsive lowspeed/hovercontrol system; and groundhandling capabilities to enable operationswithout a ground handling crew. 51The Pelican hybrid <strong>air</strong>ship builds on threeprior DARPA efforts: Walrus, Control ofStatic Heaviness (COSH), and BuoyancyAssisted Lift Air Vehicle (BAAV). Walruswas an effort conducted by DARPA/TacticalTechnology Office to define an objectivevehicle concept and provide the technicaldata to evaluate the military utility of aglobal reach vehicle. This effort culminatedin a Technology Development andAssessment Plan submitted in 2006. TheCOSH project, completed in July 2008,provided a technology demonstration of asystem that changes the density of heliumwith a flight-qualified compression system.This effort proved the concept of the heliumpressurization envelopes (HPEs) that are55
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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
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Table 22: HALE-D Program Overview .
Page 9 and 10:
EXECUTIVE SUMMARYIn the Senate repo
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for unmanned aerial vehicle and cru
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Integrated Sensor Is Structure (ISI
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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: MZ-3AVehicle Class: Conventional Ai
Page 71 and 72: Figure 53: Illustration Showing Lig
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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