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Slide 1: Integrated Sensor Is the Structure (ISIS) Distribution Statement “A” (Approved for Public Release, Distribution Unlimited) 1
Slide 2: Integrated Sensor Is the Structure (ISIS) Simultaneous AMTI/GMTI Operation via Dual Band (UHF/X-Band) Aperture Cruise Missile Defense Long-range AMTI/GMTI/COMM Detect/Track Dismounts FOPEN GMTI To Scale Global Hawk 1.0 Relative Search Capability (PA) 1.0 Relative Track Capability (PA2/λ2) X X S S UHF VHF 140 1,800 1,500 3,000 Joint STARS Platform carries the antenna AWACS Extremely High Capacity Comms Distribution Statement “A” (Approved for Public Release, Distribution Unlimited) ISIS 160,000 Platform is the antenna X 330,000,000 100 101 102 103 104 105 106 107 108 109 Global Relocation <10 days – 600km Sensor Radius – No In-Theater Ground Support 2 10+ year Operational Lifetime – 99% Availability for 1 year
Slide 3: Integrated Airship-Radar Conventional Payload: 2-3% of system mass ISIS New Paradigm Payload: >30% of system mass 89,000kg MDA Airship Payload bay Integrated Payload Enabling Technologies Hull Material Active-Array Antenna DARPA ISIS Accomplishments • Improved lifetime by 10x while reducing fabric mass 4x over state-of-the-art • • • • Performance from size, not power Removed heavy high power electronics, cooling Removed structure: Flexible panels bonded onto pressure vessel Low-power Transmit/Receive modules based on low-cost “cell phone” technology Power System • Solar-regenerative power with fuel cells instead of batteries • Airspeed: 60 knot sustained, 100 knot sprint FY06 FY07 FY08 FY09 FY10 FY11 FY12 FY13 SDD… TRL 7 MRL 6 3 FY04 FY05 System Study Technology Development Scaled Prototype System Demonstration TRL 5 MRL 2 Distribution Statement “A” (Approved for Public Release, Distribution Unlimited)
Slide 4: ISIS Critical Technologies Addressing critical hardware technology needs • Low areal-density advanced hull material – – – – Areal density ≤100 g/m2 Matrix glass transition temperature (TG) ≤ -90°C Fiber strength-to-weight ≥ 1000 kN·m/kg Fiber retains >85% strength at 5 years Achieved 90.6 g/m2 -101°C 1274 kN-m/kg >85% at 22 years Mass • Lightweight, low-power density AESA – Areal density ≤ 2 kg/m2 – Power consumption ≤ 5.0 W/m2 on receive – Bonded to hull material 1.8 kg/m2 4.7 W/m2 Passed • Extremely low-power Transmit-Receive modules – FOM ≥1x104 W-2 – Demonstrated TRL5 (MTTF >106 Hours) 1.1 x 104 W-2 MTTF >1.98x106 Hours Power • Novel power systems for stratospheric airships – Demonstrate 400 W-hr/kg regenerative system 779 W-hr/kg Distribution Statement “A” (Approved for Public Release, Distribution Unlimited) 4
Slide 5: Single Integrated Picture “High-Definition” Picture of All Moving Targets → 10x Resolution Improvement SEA LAND AIR Complete Air Picture • AWACS (70’s) and E-2 (60’s) – designed for hard targets of their day • ISIS is designed for the theoretical limit at the radar horizon – Single-platform search, track, and fire-control JLENS 225km Pulse-to-Pulse aperture reconfiguration enables all missions simultaneously Blue Water Foliage Penetration Urban Brown Water ISIS AWACS 375km 600km Global Relocation <10 days – 600km Sensor Radius – No In-Theater Ground Support 10+ year Operational Lifetime – 99% Availability for 1 year Unobscured Surface Target • Joint STARS (70’s) designed for tanks in the Fulda Gap • ISIS is designed for dismounts across the entire Line-of-Sight – LSRS-like resolution – 300km @ 3º grazing angle – 600km line-of-sight ISIS JSTARS Wide-Area Foliage Penetration GMTI • Joint STARS precision across an extremely large operational area 600km 300km 600km 300km Primary tropical forest Cerrado savanna Agriculture/pasture Natural/artificial waterbodies Secondary succession forest Distribution Statement “A” (Approved for Public Release, Distribution Unlimited) 300km – Track 600km – Detect & Locate 5
Slide 6: No Forward-Based Logistics • Forward-deployed aircraft-based ISR – – – – – – Local air base Multiple aircraft for single orbit Air crews Ground crews Fuel supplies Maintenance facilities • CONUS-deployed ISIS – – – – – – Unmanned Launched from U.S. locations Global deployment in 10 days Regenerative fuel sources Ten-year service life Permanent CONUS ground station Multiply the cost delta by the number of AOI’s and multiple platform types (JSTARS, AWACS, P-3, E-2C, etc) Distribution Statement “A” (Approved for Public Release, Distribution Unlimited) 6
Slide 7: Schedule FY04 FY05 FY06 FY07 FY08 FY09 FY10 FY11 FY12 FY13 Phase 1 Phase 1: Feasibility Study • Objective system design • Technology requirements • Sensor analysis Phase 2: System Studies and Technology Development • Continued objective system design • Develop core technology Phase 3: Demo System Design • Demo system design • Large-scale integration • Hi-fidelity flight test simulation • Demonstration system build • Flight demonstration Phase 2 Conceptual Design Review (CoDR) Phase 3 Design/Build/Demo Technology Readiness Review (TRR) PDR CDR Demo Distribution Statement “A” (Approved for Public Release, Distribution Unlimited) 7