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System F6System F6
Paul Eremenko
Tactical Technology OfficeDefense Advanced Research Projects Agency
(571) [email protected]
February 2010
Approved for Public Release. Distribution Unlimited.
http://www.darpa.mil/tto/programs/systemf6/Briefings/Overview.pptxhttp://www.darpa.mil/tto/programs/systemf6/index.html
2Approved for Public Release. Distribution Unlimited.
Program Goals
Single PayloadMonoliths
Single PayloadMonoliths
FractionatedCluster
FractionatedCluster
FractionatableMonolith
FractionatableMonolith
Status quo Payload separation with no resource sharing or closed-loop
cluster flight
Monolithic spacecraft equipped with F6 Tech Package
Heterogeneous distribution and sharing of bus & payload functions
Infr
astr
uct
ure
/Bu
s S
up
po
rt
Fu
nct
ion
Dis
trib
uti
on
Mission/Payload Function Distribution
Low High
Lo
wH
igh
MonolithMonolith
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
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Technologies
Space/ground packet-switched network with multi-level security (MLS)
Real-time avionics and mission resource sharing over space-based wireless network
Agile and semi-autonomous multi-body cluster ops
Precise relative navigation for multi-body clusters
On-Orbit Experiments
Demonstrate defensive scatter/re-gather maneuver
Demonstrate self-inspection and local-area surveillance
Simulate replacement of spacecraft control processor by effecting ADCS control from another spacecraft
Perform outer-loop control of a spacecraft from a terrestrial network node
Simulate replacement of a star-tracker by determining and sharing relative attitude from another spacecraft
Show efficient, semi-autonomous cluster reconfiguration to accommodate a new spacecraft module
Demonstrate ability of third-party payloads to utilize existing on-orbit infrastructure services
Warfighter Needs
SURVIVABILIT
Y
OPERABILITY
RESPONSIVENESS
Technologies, Experiments, and Needs
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4
Flexibility
ScalabilityAbility to scale system functionality in response to demand volatility. Ability to deploy incrementally.
Ability to create systems bigger than launch capability.
EvolvabilityAbility to respond to technological obsolescence
through mid-life deployment of new functionality
AdaptabilityCluster reconfiguration can enable new functionality
once system is on orbit
MaintainabilityAbility to replace failed modules throughout the
system’s lifecycle
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5
SurvivabilityGraceful 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 ToleranceGraceful degradation of system functionality in
response to failure
Robustness
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6
Payload IsolationRequirements decoupling across multiple payloads
Simplified IA&TReduced undesirable/unmodeled interactions during
integration, assembly, and test (IA&T). Geographically-dispersed integrated testing.
Reduced Barrier to EntryEnables small satellite manufacturers to create or
participate in development of large systems. Increased number of competitive opportunities.
Production LearningMass production and learning effects across “infrastructure” modules may reduce unit costs
Other Attributes
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7
F6 PayloadModule
F6 InfrastructureModule A
F6 InfrastructureModule B
F6 Tech Demo •Self forming wireless network•Distributed resource sharing•Transfer of critical functionality•Commanded cluster geometries•Defensive “scatter” maneuvers•Demo payload operation
3rd Party Launch Launch of ORS/AFRL
SARSat to common orbit
3rd Party Module Entry •Network authentication•Autonomous cluster entry•Fully functional payload operation
ORS SARSat (3rd Party) Module
TerrestrialInfrastructure
Third-Party Components
High-Bandwidth Wireless Links
Wired Links
Relative Nav Sensing
LEGEND
F6 Demo Launch All three demo modules launched on dedicated
Minotaur-IV
Hosted SSAEM Payload
• Hi Data Rate Ground Comm• Mission Processor
• 24/7 GEO Comm Relay • Mission Processor
Robust to ground interference
Relative navigation
Multi-levelinfo assurance
security
Packet-level encryption
GEOComm Relay(Optional 24/7
TT&C)
1
2
3
4
Low-Bandwidth Wireless Links
Ground controlsystem
Payloadtasker/user
INTERNET/SIPRNET
SustainmentAdditional payload and
infrastructure modules for future operational capability
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Hypothetical LEO Demo Scenario
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8
F6 Module AGEO Communications
SatelliteThird-Party Components
High-Bandwidth Wireless Links
Wired Links
Relative Nav Sensing
LEGEND
F6 Demo Launch Two F6 demo modules
launched as rideshare on STP EELV ESPA ring
Co-Orbital Slot Entry •F6 modules enter GEO slot of F6-enabled ComSat
•Network authentication•Cluster geometry formation
F6 Tech Demo •Self forming wireless network •Distributed resource sharing•Transfer of critical functionality•Commanded cluster geometries•Defensive “scatter” maneuvers
Hosted F6 Tech Package
Robust to ground interference
Relative navigation
Packet-level encryption
• Missile Warning IR Payload• Backup Subsystem
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2
3
SustainmentAdditional payload and
infrastructure modules for future operational capability
4TerrestrialInfrastructure
F6 Module B• LaserComm Payload• Upgraded Subsystem
Multi-level info assurance security
Geosynchronous Orbit
Ground controlsystem
Payloadtasker/user
INTERNET/SIPRNET
Hypothetical GEO Demo Scenario
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9
Military Utility Summary
Development
Launch
Operations
Retirement
Development Semi-AutonomousOperations
TIME
TIMEFRACTIONATED
MONOLITHIC
$
$
Semi-AutonomousOperations
IncrementalDeployment
ComponentUpgrade
LifeSustainment
FLEXIBILITY
ROBUSTNESS
Increased Cost
Development
NominalLaunch
Operations
RetirementLaunchFailure Rebuild Relaunch
Increased Cost
Development
IncrementalDeployment
Semi-AutonomousOperations
LaunchFailure
Rebuild/Relaunch
TIME
TIME
$
$
FRACTIONATED
MONOLITHIC
On OrbitFailure
On Orbit Failure
Cost
Utility
Payload Delay
Launch Failure
On Orbit Failure
Decreased Utilitydue to:
Cost
Utility
MISC ATTRIBUTESLaunch Retirement / Launch
TIME
$
$ Launch
Payload ModuleFailure Event
FRACTIONATED
MONOLITHIC
FailureEvent
Rebuild
Relaunch
Smaller per-module NRE reducesspace industry barrier-to-entry
Requirementsdecoupling between modules simplifies IA&T for large systems
Residual on orbitinfrastructure requiresre-launch of payload only
TIME
PlannedReconstitution
PlannedReconstitution Relaunch
Cost
Utility
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Program Schedule
Tasks FY08 FY09 FY10 FY11 FY12 FY13 FY14
Phase 1: Concept & System Development
Phase 2: Detailed Design
Phase 3: Integration, Assembly, and Test
Phase 4: Launch Integration & Demo
PDR = Preliminary Design ReviewCDR = Critical Design Review
Third-PartyResidual Ops
Launch1
Launch 2(TBD)
Third-PartyLaunch
PDR andGo/No-Go
HIL1 HIL2(* All principal designfeatures simulated)
HIL3*
CDR andGo/No-Go
HIL4(** All software written, keyhardware breadboarded)
HIL5**
FRR andGo/No-Go
HIL6 HIL7*** HIL8
Third-PartyHIL Demo
(*** All software qualified,all hardware in EDUs)
FRR = Flight Readiness ReviewHIL = Hardware-in-the-Loop Demo
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Fractionated Space System Architecture
