on-board networks in space systems - irit · this document and its content is the property of...

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On-board networks in space systems WFCS 2014, May 5th, Toulouse, France

Olivier Notebaert Airbus Defence and Space Space Systems – Central engineering Toulouse Office Z#012 - [email protected]

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Outline Spacecraft systems Communications needs and constraints On-board architecture

Space systems on board networks Current technologies Future needs and technologies

IEEE International Workshop on Factory Communication Systems WFCS 2014, May 5th, Toulouse, France

On-board networks in space systems

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Pleiades

Spacecraft systems

Satellites Observation Science Telecommunications Navigation



© ASTRIUM

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Spacecraft systems




Alphasat I-XL communications satellite © ASTRIUM

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Spacecraft systems


Space exploration Cruise vehicles Specific manoeuvers Surface exploration (rovers)



Bepi Colombo release at Mercury © ASTRIUM

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Spacecraft systems





EXOMARS rover © ESA

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Spacecraft systems



Space Transportation Orbit service vehicles Manned Flight Launchers



International Space Station and ATV-2 Johannes Kepler © NASA

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Ariane 5 launch of EUTELSAT 21B & STAR ONE C3

Spacecraft systems



Space Transportation Orbit service vehicles Manned Flight Launchers



© CNES © ESA-CNES-ARIANESPACE

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Communications needs and constraints

Data handling functions Communications with ground Vehicle Guidance, Navigation and control Payload control, data processing and

on-board storage Mission management Spacecraft equipment housekeeping Fault management

On-board Systems constraints Space environment Industrial efficiency



Curiosity explores the surface of MARS © NASA

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Data Handling functions Communications Communications with the Ground segment Telecommand (TC)

– Low data rate – Survival mode (commanding capability guaranteed with minimal on-board resources)

Telemetry (TM) – Low rate mission control and housekeeping data – High rate payload data

Availability of ground-board communications is variable – Permanent in Geostationary Earth Orbit – Submitted to visibility windows in Low Earth Orbit or in deep space

Communication Standards CCSDS (Consultative Committee for Space Data System)

Joint organisation with participation of major space agencies (NASA, ESA, JAXA,...). International interoperability standard for TC/TM



On board communications resource RF communications equipment • Analog <> Digital On board data links: • Point to point • Buses and networks

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Data Handling functions Vehicle Guidance, Navigation and control Knowledge and control of the systems position and attitude Guidance, Navigation, Attitude and Orbit Control Instrument and antennas pointing Interactions between the Spacecraft Platform, solar panels and instruments

Maintenance of operational parameters in the functional domain Thermal control

– thermal sensors on structure and equipment, heaters control Power system control

– battery management, solar panels control and orientation, power distribution Operational Modes Control Orbit transfer mode Nominal mode Survival mode

– Easy attitude control (e.g. sun pointing) – Limited power consumption – Minimal TC/TM communications



Low rate and highly deterministic command-control bus (e.g.1553)

On board communications resource

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Data Handling functions Payload control, data processing and on-board storage Observation & Science Image & Radar processing (compression, ciphering…) Scientific data processing Mostly data stream processing few missions with real-time control loops

Telecommunications Modulation, Demodulation, (de)ciphering, Channel Switching

Main characteristics Huge data volume High capacity modular compression and mass memory units Specific Payload data processing and control systems

Ad-hoc data network architecture • High speed point-to-point data links • On board data networks • Command control bus (1553 or Can bus)

On board communication resource

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Data Handling functions Mission Management System operation TC/TM for remote operations and mission control Mission phase, Modes, and events Management On-board mission data storage On-board mission SW maintenance

Mission autonomy On-board operations scheduling (mission plan or time-tagged commands) On-board automated procedures

Low rate command-control bus (e.g.1553)


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Data Handling functions Spacecraft equipment management Equipment configuration and calibration Housekeeping Monitoring equipment health parameters Triggering Fault Management service in case of non nominal operations

In-orbit on-board software maintenance Type of equipment

Simple devices (without processing capability) Sun Sensors, reaction wheels, simple gyroscopes or optical sensors… Smart devices (with processing capability) On-board computers, Mass memories,… Inertial measurements systems, Star sensors,

GNSS devices, Gyroscopes…

• On-board Networks (SpaceWire) • On-board real-time data buses (1553, Can bus) • Sensor networks (Can, I2C,…) • Direct analogue or digital interfaces


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Data Handling functions Fault Management

Source of faults Electrical, electronic or mechanical element Software error External event (space debris, meteorite, …) External disturbance (electro-magnetic effect, solar flares…) Operational fault (or intentional attack)

Capacity to detect, isolate and report faults Fast and correct diagnosis Prevention of propagation or amplification through a looped system

Capacity to configure the Spacecraft into a survival mode Capacity to restore nominal operations With the minimum data losses & availability level

On board communication resource • On-board Networks (SpaceWire) • On-board real-time data buses (1553, Can bus) • Sensor networks (Can, I2C,…) • Direct analogue or digital interfaces

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Spacecraft systems constraints Communications Limited data rates and short communication windows Low availability except in GEO On-board data storage and compression On-board TC/TM data processing for bandwidth optimisation Smart TM (autonomous selection of useful and focused data) Automated on-board procedures and operation scheduling

Synchronisation Time reference (e.g. GPS) Accuracy of time distribution and synchronisation on board Synchronisation with distant systems (ground stations, other spacecrafts)

Robustness and security Operator error robustness Ciphered data en/de-coding, TC authentication

Services More communication paths, including between spacecrafts



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Spacecraft systems constraints Environment Tolerance to radiations for on-board electronics Cumulated radiation dose limits time-life + Destructive effects (latch-up) + Transients errors

due to space particles (heavy ions, protons…) Rad hard component technologies (e.g. Silicon On Isolator) Fault-tolerant design inside the chips Fault-tolerant systems architecture with COTS components Poor electronics components and devices catalogue Lower processing performance w.r.t. ground applications Complex systems, heavy investments Solar Energy only Mechanical constraints Vacuum and thermal variations Operation conditions: Assembly Integration and Tests, transport, launch, in-orbit…



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Spacecraft systems constraints Industrial efficiency

Variety of missions Generic platforms: Requirement domain without precise mission selection Standard Product families: Customisation for adaptation to mission

Make or Buy decision Interfaces standardisation, inter-operable products catalogue International partnerships, ITAR constraints

Testability Complexity of systems makes full test coverage difficult Improvement of production, integration and validation methods and tools

Quality Cost of non-quality is difficult to predict Demanding quality requirements

Obsolescence Maintenance of critical components manufacturing capability Strategic stocks

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Spacecraft systems on-board architecture Satellites Two subsystems Payload Instruments Data Processing

– Mission specific (science instruments…)

– Huge data volumes – High speed data links – Non-real time Data

Platform Command and Control & Data Handling

– Mostly generic – Low data volumes – Low speed data bus – Real-time constraints



METOP Platform TERRASAR Platform

Performance

Reliability

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Spacecraft systems on-board architecture Satellites

Power Control & Distribution

Battery

Electrical Power

gyroscopes magnetometer

sun sensor

Sensors

star trackers magnetic torquers

Actuators

thrusters

Attitude and Orbit Control System (AOCS)

wheels

Control Momentum Gyroscope

Solar Panel Deployment

Mechanisms

… On-board Real-Time Networks

Data management System

Data Storage

Data Storage

Central Software

Central DMS

Central Computer

Thermal Regulation

Thermal Control Electronics

Thermal sensors

Heaters

Fluid loops

Thermal Regulation


Thermal sensors

Heaters

Fluid loops

Thermal Regulation


Thermal sensors

Heaters

Fluid loops

Payload processing

Payload Software

High performance Computer (s)

instruments

Transponders

RF Communications

Transponders

Antennas

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Spacecraft systems on-board architecture Satellites Platform Data Handling

To dumb sensors (>100): Thermistors, switch closure…

Central On-Board Computer

Main system bus

Point-to-point Connections or connection to Main system bus

To smart sensors (<10): Reaction wheels, star trackers, Gyroscopes, GPS receiver…

Remote Terminal

Analogue interfaces

Remote Terminal

Remote Terminal

Remote Terminal

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Spacecraft systems on-board architecture Payload data processing functional chain

Data Storage

Instrument or antenna Data Receiving Data Processing Data

Transmission Antenna

Payload Control

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Spacecraft systems on-board architecture Typical scientific spacecraft architecture

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Spacecraft systems on-board architecture Launchers Fully automated system Stages separation Guidance Navigation and Control Generic equipment with specific mission

configurations Low data volumes Critical real-time constraints High Availability Low speed data bus

Telemetry system High data volumes Segregated from the GNC system



SIGNAL DE BONFONCTIONNEMENT

EQ.Nominal N°1

EQ.Nominal N°i

EQ. RedondantN°1

EQ. RedondantN°i

OBSERVATION DU CONTEXTEET REPRISE EN CAS DE

DEFAILLANCE DEL’OBC MAITRE

OBC 1(Maître)

UCTMCOUPLEUR

VERS ETAGES INFERIEURS

BUS 1 BUS 2

OBC 2(Secours)

ENVOI DES ORDRES,ACQUISITION DES MESURES,

AUTOTEST.INHIBITION EN CASDE DEFAILLANCE

VERS ETAGES INFERIEURS

MIL-STD-1553B

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Rendez-vous Sensors

SENSORS ACTUATORS

VTC CMU

FTC 1

ATV CORE

SYSTEM BUSES

RUSSIAN SEGMENT BUSES

FTC 2 FTC 3

US SEGMENT BUSES

CMU

Launch Pad i/f BUSES

CMU

Equipment Measurement & Command

MSU

ATV CARGO

Propulsion Drive

Electronics Gyros Earth

Sensors

GPS Power Distr.

UHF S Band

Sun Sensors

to CMUs



Spacecraft systems on-board architecture In Orbit service & manned flight (ATV)

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… now lets focus on networks technologies …

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Outline Spacecraft systems Needs and constraints On-board architecture

Space systems on board networks Current technologies Future needs and technologies



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Networks Technologies Spacecraft applications Sensors and actuators Connections to local Remote Terminals or directly to on-board computer

– Typical bandwidth: 10 to 100 Kbps – New sensors with higher data rates (10 to 100 Mbps or more)

System bus for spacecraft control Main data link between the on-board functional sub-systems Driven by a central computer Key properties: determinism, dependability Typical bandwidth: 0,1 to 1 Mbps

Payload data Instruments data processing and storage Typical bandwidth: 100 Mbps to 1 Gbps, sometimes more

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Networks Technologies Space standards Several data links standards in space Payload data (RS-422, 1355, SpaceWire, Ethernet,…) Command and control (OBDH, Can, MilBus 1553,…) Sensor buses (I2C, Can bus,…) and analogue dedicated interfaces (Direct commands, sensor acquisition…)

Trade-off drivers Technologies adaptation to environmental constraints Performance, quality of service, real-time determinism Electrical robustness (BER, EMC) Built-in fault tolerance (reliability, redundancies,…) Power consumption, Overall Weight/length of cables Cost of terminals SW drivers complexity

Standardisation of on-board data links ECSS (European Cooperation for Space Standardisation) European interoperability and technology harmonisation Promoting mainly MIL-STD-1553 and SpaceWire Also Can bus, RS-422 are currently used

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Networks Technologies Mil-Std-1553 bus Well adapted for spacecraft command and control Very good reliability characteristics Allows deterministic and efficient real-time command/control Lot of sensors, commercial products and test equipment Large return on experience in space applications

Used for many European space applications Launcher avionics on Ariane 5 and Vega Spacecraft command and control for platforms and payloads Attitude and Orbit Control systems In-Orbit infrastructure and manned flight for ISS and ATV Industrial baseline on almost all space on-board data systems

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Networks Technologies Mil-Std-1553 bus architecture overview Master/Slave concept with 2 types of nodes One Master Bus Controller (BC)

– Unique initiator for any data transfers – Manages the bus configuration through specific commands

Up to 31 Remote Terminals (RT) – Slaves: cannot emit any data on the bus without a Bus Controller request

Protocol control with a status for every bus transaction ECSS standard configuration requirements and communication services protocol

BC

RT 1 RT 2 RT 3 RT 31

To sensors/actuators

● ● ●

To Data Handling System

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Networks Technologies SpaceWire Well adapted for spacecraft payload data communication Derived from IEEE 1355 LVDS, Point to point connections, 200Mbps Network capability, definition of switches, wormhole routing… Remote Memory Access Protocol for Peer to peer communications ECSS standard

Used in many spacecraft development worldwide Europe, US, Japan, Canada, Russia, China,… Point to point SpW links on many spacecraft such as Gaia or James-Webb

Telescope On-board network: Bepi-Colombo, Solar Orbiter Active user community (Spacewire working group and International Conference)



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Networks Technologies Future needs Current situation 1553 for platform and payload control SpaceWire for Payload data Sometimes Can bus (in development for telecom) Specific links on some interfaces… when preferred

Stakes Data rates and volumes increase drastically with instruments technologies and new

applications while ground space communications are highly constrained Central computer will have to perform more functions and communication protocols shall not

take too much computing resource Cost increase for software and tools due to a lack of standardisation and variability on buses

and protocol will no more be acceptable Equipment will need high performance real-time data exchanges and close loop automation.

They will have to be configured, uploaded, controlled and commanded The overall bandwidth and the number of connected equipment will increase Interoperability and easy configuration will be required Qualification and certification issues



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Networks Technologies Future needs Requirements

MORE PERFORMANCE Bandwidth, low latency, determinism,… SIMPLE Easy to configure assemble and test, Interoperable, Reconfigurable, Scalable,… Mix critical real-time control data and high throughputs

Main limitations with current space standards 1553

– Power consumption – Cost of terminals – Non scalable with a limited number of terminals – Limited bandwidth with respect to future needs

SpaceWire – Wormhole routing, real-time limitations – Risk of network congestion – Verification issue with complex networks – Limited bandwidth with respect to future needs

Considered standards in other application domains Switch Ethernet protocols (AFDX, TTEthernet,…), Flexray,…



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Networks Technologies Current developments for future space applications SpaceWire Standard improvements (SpW Rev-1) New protocols (SpW-D, SpW-RT) SpaceFiber ( > 1 Gbps with SpW compatibility) Spacewire networks for AOCS

Can bus Simplification of future telecom platfomrs and payload TM/TC system

AFDX MISSION projects - spacecraft avionics evolution

Time-Trigerred Ethernet AvionicX – for future launchers OBC-SA – for satelites and robotics applications

Others Network architecture and FDIR issues (e.g. N-Mass ESA study) Network modelling (e.g. MOST for SpaceWire) Analysis tools for validation (e.g. Formal methods for schedulability analysis) Miniaturization / Integration of I/O protocols in HW (e.g. IO controller CNES study)



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Scientific platform use case topology with AFDX

Mission project (FP7) Methodology and assessment for the applicability of ARINC-664 (AFDX) in Satellite/Spacecraft on-board communicatION networks Analyze and adapt requirements for introducing ARINC-664 (AFDX) in satellite/spacecraft

on-board data networks Define network centric approach architecture for spacecraft based on European Space

Agency reference architecture from SAVOIR working group and operational missions to provide the network topology and the data profile

Design and develop ARINC-664 (AFDX) configuration and traffic profiles for space Develop and validate a representative ARINC-664 (AFDX) over Ethernet ground

demonstrator of the on-board architecture Develop and validate a representative ARINC-664 (AFDX) over SpaceWire ground

demonstrator of the on-board architecture

Networks Technologies AFDX



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Networks Technologies Time Triggered Ethernet for launchers ESA roadmap for developping TTEthernet technology



SW

SW

SW

ES2

ES3

ES1

SW

ES2’

E3’

ES1’

ES4’

GTW

ES5

ES4

ES6

ES5’

ES6’

ES7’

ES8’

ES7

ES

8

Performance (at least 100 Mbits/s)

TTEthernet features Targets for Ariane 6

Margin / Simplified FSW

Time-Triggered traffic Verification/Validation Effort reduced

Ethernet compatible Ground operations simplification

Isolation of traffic TT, RC, BE

Merge of previously (A5) segregated data flow

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Summary On-board networks in space systems

Very high diversity of space applications Different types of links, ad-hoc architecture and variability of implementations Standardisation and technology harmonisation – 1553 and Spacewire are most

used today Technology harmonization shall continue: reference architectures and building

blocks

Communication technology needs in future space applications Needs for higher bandwidth and critical real-time support, Scalability and easy configurability Many studies are on-going to consolidate needs and evaluate existing ground

standards Switch Ethernet based solutions (AFDX, TTEthernet) are considered promising



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Thank you for your attention !

Questions ?

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Links www.airbus-group.comt

www.astrium.eads.net www.spacewire.esa.int

www.ecss.nl [email protected]

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