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System F6

http://www.darpa.mil/tto/programs/systemf6/Briefings/Overview.pptx http://www.darpa.mil/tto/programs/systemf6/index.html. System F6. Paul Eremenko Tactical Technology Office Defense Advanced Research Projects Agency (571) 214-2436 paul.eremenko@darpa.mil February 2010.

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System F6

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  1. http://www.darpa.mil/tto/programs/systemf6/Briefings/Overview.pptxhttp://www.darpa.mil/tto/programs/systemf6/Briefings/Overview.pptx http://www.darpa.mil/tto/programs/systemf6/index.html System F6 Paul Eremenko Tactical Technology Office Defense Advanced Research Projects Agency (571) 214-2436 paul.eremenko@darpa.mil February 2010 Approved for Public Release. Distribution Unlimited.

  2. Program Goals FractionatableMonolith Single PayloadMonoliths Fractionated Cluster • Replace monolithic satellites with wirelessly-networked, resource-sharing clusters • Develop & demo safe, efficient, and autonomous multi-body cluster flight techniques • Develop & demo secure/robust real-time distributed avionics capability over wireless links • Demonstrate a cyber security hardware/software paradigm to fortify the distributed and shared information infrastructure • Develop an F6 Developer’s Kit providing open interface standards & reference designs • Develop 24/7 LEO-to-ground communications capability • Develop a value-centric design and acquisition tool set High Heterogeneous distribution and sharing of bus & payload functions Monolithic spacecraft equipped with F6 Tech Package Infrastructure/Bus Support Function Distribution Monolith Low Payload separation with no resource sharing or closed-loop cluster flight Status quo Mission/Payload Function Distribution Low High

  3. Technologies, Experiments, and Needs Approved for Public Release. Distribution Unlimited.

  4. Flexibility Scalability Ability to scale system functionality in response to demand volatility. Ability to deploy incrementally. Ability to create systems bigger than launch capability. Evolvability Ability to respond to technological obsolescence through mid-life deployment of new functionality Maintainability Ability to replace failed modules throughout the system’s lifecycle Adaptability Cluster reconfiguration can enable new functionality once system is on orbit Approved for Public Release. Distribution Unlimited.

  5. Robustness Survivability Graceful degradation of system functionality in response to hostile acts. Target spreading. Signature reduction. De-correlation of failure events across the system (e.g., “architectural self-insurance” during launch). Fault Tolerance Graceful degradation of system functionality in response to failure Approved for Public Release. Distribution Unlimited.

  6. Other Attributes Simplified IA&T Reduced undesirable/unmodeled interactions during integration, assembly, and test (IA&T). Geographically-dispersed integrated testing. Payload Isolation Requirements decoupling across multiple payloads Reduced Barrier to Entry Enables small satellite manufacturers to create or participate in development of large systems. Increased number of competitive opportunities. Production Learning Mass production and learning effects across “infrastructure” modules may reduce unit costs Approved for Public Release. Distribution Unlimited.

  7. Hypothetical LEO Demo Scenario 2 4 • F6 Tech Demo • Self forming wireless network • Distributed resource sharing • Transfer of critical functionality • Commanded cluster geometries • Defensive “scatter” maneuvers • Demo payload operation LEGEND • 3rd Party Module Entry • Network authentication • Autonomous cluster entry • Fully functional payload operation GEOComm Relay(Optional 24/7TT&C) Third-Party Components Wired Links Low-Bandwidth Wireless Links High-Bandwidth Wireless Links ORS SARSat (3rd Party) Module Relative Nav Sensing F6 Infrastructure Module A Packet-level encryption • 24/7 GEO Comm Relay • Mission Processor Multi-levelinfo assurancesecurity Relative navigation Robust to ground interference F6 Payload Module Hosted SSAEM Payload F6 Infrastructure Module B • Hi Data Rate Ground Comm • Mission Processor 5 Sustainment Additional payload and infrastructure modules for future operational capability 1 F6 Demo Launch All three demo modules launched on dedicated Minotaur-IV Terrestrial Infrastructure 3 3rd Party Launch Launch of ORS/AFRL SARSat to common orbit Payloadtasker/user INTERNET/SIPRNET Ground control system Approved for Public Release. Distribution Unlimited.

  8. Hypothetical GEO Demo Scenario LEGEND F6 Module A GEO Communications Satellite 2 Hosted F6 Tech Package • Missile Warning IR Payload • Backup Subsystem • Co-Orbital Slot Entry • F6 modules enter GEO slot of F6-enabled ComSat • Network authentication • Cluster geometry formation Third-Party Components Packet-level encryption Wired Links High-Bandwidth Wireless Links Relative navigation Relative Nav Sensing Multi-level info assurance security 3 • F6 Tech Demo • Self forming wireless network • Distributed resource sharing • Transfer of critical functionality • Commanded cluster geometries • Defensive “scatter” maneuvers Robust to ground interference Geosynchronous Orbit F6 Module B • LaserComm Payload • Upgraded Subsystem 4 Terrestrial Infrastructure 1 Sustainment Additional payload and infrastructure modules for future operational capability F6 Demo Launch Two F6 demo modules launched as rideshare on STP EELV ESPA ring Payloadtasker/user INTERNET/SIPRNET Ground control system Approved for Public Release. Distribution Unlimited.

  9. Military Utility Summary Increased Cost FailureEvent $ Relaunch Launch Retirement / Launch MONOLITHIC TIME Rebuild Payload ModuleFailure Event PlannedReconstitution PlannedReconstitution $ Increased Cost Launch Relaunch FRACTIONATED TIME Residual on orbitinfrastructure requiresre-launch of payload only Requirements decoupling between modules simplifies IA&T for large systems Smaller per-module NRE reducesspace industry barrier-to-entry NominalLaunch LaunchFailure On OrbitFailure Retirement Rebuild Relaunch FLEXIBILITY $ $ MONOLITHIC Development TIME Launch Retirement Operations ROBUSTNESS MONOLITHIC Development TIME Operations Decreased Utility due to: Payload Delay IncrementalDeployment Launch Failure Rebuild/Relaunch On Orbit Failure Launch Failure On Orbit Failure $ $ Utility Utility Utility IncrementalDeployment ComponentUpgrade Life Sustainment MISC ATTRIBUTES Cost Cost Cost FRACTIONATED FRACTIONATED Development Development TIME Semi-AutonomousOperations Semi-AutonomousOperations TIME Semi-AutonomousOperations Approved for Public Release. Distribution Unlimited.

  10. Program Schedule CDR and Go/No-Go HIL4 HIL5** (** All software written, key hardware breadboarded) FRR and Go/No-Go HIL6 HIL7*** HIL8 Third-Party Residual Ops (*** All software qualified, all hardware in EDUs) Third-Party HIL Demo Launch1 Third-Party Launch Launch 2 (TBD) PDR and Go/No-Go HIL1 HIL2 HIL3* (* All principal design features simulated) PDR = Preliminary Design Review CDR = Critical Design Review FRR = Flight Readiness Review HIL = Hardware-in-the-Loop Demo Approved for Public Release. Distribution Unlimited.

  11. Fractionated Space System Architecture

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