astrium satellites central engineering – dependability, data processing and software division...

Astrium Satellites Central Engineering – Dependability, Data Processing and Software Division (ASG7)

[email protected]

12006 MAPLD International Conference SpaceWire 101 Seminar

ESA missions, a view from EU Primes

SpaceWire 101 Seminar2006 MAPLD, International ConferenceWashington, D.C, USA - September 25, 2006

High speed data links on recent European spacecrafts

High speed data links on future missions

Olivier NOTEBAERT / Hubert Pelon – Astrium Satellites, France



High speed data links on recent European spacecrafts (ESA) Rosetta Mission

A 10-years long cruise toward the comet

67P/Churyumov-Gerasimenko Fly-by at least one asteroid during the cruise

phase. In-orbit comet scientific observations during

one year down to the comet perihelion Land smoothly on the comet surface a

Science Package (named RoLand) for in-situ measurements

Launched in 2004

Initial scenario with comet Wirtanen and asteroids flybys



High speed data links on recent European spacecrafts (ESA) Rosetta: On board communications

Standard Avionics Command Control on OBDH

Remote Terminal Units on OBDH with discrete links to instruments (11 P/L instruments)

IEEE 1355 serial data link between the different data processing nodes and the Solid State Mass Memory 2 P/L Instruments (VIRTIS@400Kbps, OSIRIS@4Mbps) Navigation camera 4 Avionics processor modules (5Mbps, redounded) Redounded link to Transfer Frame Generator for telemetry

Mass memory access with File management System



High speed data links on recent European spacecrafts (ESA) Rosetta Architecture

1355 (SpaceWire) links



High speed data links on recent European spacecrafts (ESA)Mars Express and Venus Express

Planetary exploration missions Five to six month cruise followed by

in-orbit planetary observation

Large reuse of the Rosetta spacecraft design New instruments connected to the S/C

Mass Memory through 1355/SpaceWire links

On Mars Express: High Resolution stereoscopic Camera

producing 25Mbps of digitalised and

compressed data (HRSC)

On Venus Express The Camera includes a Digital

Processing Unit (Xilinx/Leon-2 processor

@20MHz) and provides up to 2.5 Mbps

data

Processed image from the Mars express HRSC © ESA

High Resolution Stereoscopic Camera on Mars express HRSC



High speed data links on future missions General trend for future missions

New missions call for new requirements Robotics, Autonomy, Security, formation flying… New instruments technology generates more on-board data

(and TM rates cannot increase accordingly) SW development techniques raises CPU use & data volumes

General increase of on-board data processing needs (performance, volumes and transfer rates)

Need for overall budget reductions Power consumption reduction Mass and Volume reduction Operational costs: reduction of the satellites dependence beside

ground (i.e. mission autonomy) Manufacturing delay reduction (parallel development, AIT) Costs

Technology upgrade enforcing re-usable solutions



High speed data links on future missions Functional Architecture and Performance Requirements

Very large scale of functions and performances We can define generic data processing functions

Communications (on-board, between spacecrafts, with ground)

Command and Control

Failure Detection Isolation and Recovery

Autonomy

Need to cope with different properties… Wide range of spacecrafts bus and instruments performances

Reliability, Availability, Safety issues

Operational and maintenance requirements

Mission profile (Technology constraints, Qualification levels…)

MODULAR ARCHITECTURENeed for a scalable set of HW and SW building blocks

interconnected on a flexible architectural system



EVOLUTIVE TECHNOLOGYNeed to focus the necessary development efforts on

a limited set of standardised solutions

High speed data links on future missions Main Constraints

Harsh environment (Radiations, Mechanics, Thermal…) Induces high costs for development and qualification programs Mission and phase dependant (Launch, Orbital, Deep space, landing…) Limited resources in space for embedded electronics

Communication Link (rates and delays)

Power budget (electrical and propulsion)

Mass and volume (launch cost, life-time…)

Fast evolution of the technologies induces obsolescence risks

Evolution of systems needs for the development of new functions and performance range



High speed data links on future missionsPayload data processing reference architectures

Performance oriented architecture Independent instruments data processing units chains Full availability of data-link bandwidth through direct interfaces to

Mass Memory for high rate science data Instrument control through system bus and Remote Terminal

Units (RTU)

Low rateDigital I/F

-DiscreteInterface

High rateDigital I/F

Low rateDigital I/F

-DiscreteInterface

Control &Monitoring

drivers

Sensors

Mechanisms

Thermal

InstrumentData

ProcessingUnit

Instrument electronics

Mass MemoryUnit

RTUelectronics

System bus

High rateDigital I/F

Low rateDigital I/F

-DiscreteInterface

OBMU

TFG

Spacecraft DataProcessing

Unit

Suitable for high rate and heavy processing on P/L data



High speed data links on future missionsPayload data processing reference architectures

Resource optimisation oriented architecture Instrument pre-processing chains connected to SpaceWire

Network Share of common data processing functions and resources Lower number of nodes and links variants Can be combined with platform avionics resources

DigitalInterface

(Spacewire)

DigitalInterface

(Spacewire)Control &Monitoring

drivers

Sensors

Mechanisms

Thermal

First-stageData

Processing

SpaceWireRouting unit

Shared DPU

Instrument electronics

Mass MemoryUnit

Data ProcessingUnit

To TFG

To/fromS/C Platform

RemoteTerminalInterface

Suitable for multi instruments P/L and medium data processing requirements



High speed data links on future missions Bepi-Colombo mission characteristics and main drivers

Mercury exploration mission Composite vehicle built through

European-Japanese cooperation

Main Modules: MPO & MMO

Mercury Planetary Observer (ESA)

Mercury MagnetosphericOrbiter (JAXA)

High level of autonomy5 to 6 years long cruiseincluding Moon, Venusand Mercury Fly-by’s.

Complex Payload11 instruments for datacollection in several scientificareas (50Mbps overall sciencedata rate and 115Kbps C&C)

Launch ~2012

Launch andearly operations

Coast arc

Trajectorycorrection

Venusflyby (x 2)

Thrust arcs(after Venus)

Coast arc


Mercuryflyby (x 2)


SEPMjettison

S U N

MPOorbit

MOI

TheEarth

Venus

M e r c u r y

Opposition

Conjunction

CPMjettison

Insertionorbit

MoonLunarflyby

Thrust arc(before the Moon)

Earthflyby

TrajectorycorrectionBepi-Colombo initial mission scenario



High speed data links on future missions Bepi-Colombo MPO proposed data links architecture

Platform Central Computer (OBMU) Platform C&C via 1553B

and direct I/O system Interface to MMO through MIL-1553B

repeaters adapted from Ariane 5

Payload Data Processing (PDPU) Science data acquisition On-board processing Compression and storage PacketWire link to TM

P/L interface with SpaceWire links Networked I/F with router for low-rate

instruments Direct links for higher rate instruments P/L C&C over SpaceWire links

BC3

(OBMU)

I/O

PDPU

Platform

Sys

tem

bu

s (M

IL-S

TD

-155

3B)

SpaceWire

links

SpaceWire Network

X-TXKa-TX

Bus I/F

MemoryProcessor(ERC32)

Sys_MM8 Gb

Sci_SSMM256 Gb

TFG

SpaceWire PacketWire

OBMU

I/O

PDPU

Repeaters

SpW router

Sys

tem

bu

s (M

IL-S

TD

-155

3B)

X-TXKa-TX

Bus I/F

Payload(11 instruments)

MemoryProcessor(ERC32)

SSMM8 Gb

SSMM 256 Gb

TFG

MMO

MPO



High speed data links on future missions GAIA mission characteristics and main drivers

Astronomy science mission Lagrangian L2 point orbital position Very high stability and fine pointing Optical instrument with high data

processing capability (data reduction) Launched foreseen in 2012

Key drivers Modularity Ease of AIT & operations Performance of video processing chain Performance of Attitude and Orbit control

Main data processing challenges Video processors (>1000Mips) On-board data reduction and storage High rates of data from P/L instrument



High speed data links on future missions GAIA proposed data links architecture

Payload Module Video Processing Units (VPU)

Optical Data Front end processingand data reduction

Data output on direct SpaceWire links

Payload Data Handling (PDHU) Science data acquisition, final

processing and storage SpaceWire links to TM through CDMU

internal Router

Service Module Central Distribution and Monitoring

(CDMU) Routing of SPW P/L science data to TM Link with I/O system through SpaceWire Command control with MIL-STD-1553

Avionics system (SVM bus) Payload bus

AOCS

EIU

CDMU

HK TMdata storage

(8 Gb)

BusI/F

BusI/F

TT&C

µPropulsionPower

Service Module

I/O

VPU

VPU

VPU

VPU

VPU

VPU

VPU

Opticalterminal

Sciencedata storage

(700 Gb)

CDU

PDHU

Payload Module

Synch

Synch

SpaceWire MIL-STD-1553

SVM bus

Pay

load

bus

TM

TC



High speed data links on future missions Conclusion for SpaceWire application

SpaceWire provides a standard solution supporting the need for high data processing performance on future spacecrafts It provides a standard data link for acquisition of a large range of

payloads which is used worldwide It allows simple devices memory access with RMAP protocol It supports CCSDS TM/TC packet routing between intelligent

terminals (e.g. complex instruments, star-trackers…) It provides a solution for on-board Network

Optimisation of on-board resources

Infrastructure for future on-board data processing performance increase

It supports the reference architecture for Payload Data Processing European Harmonization Contributes to the development of generic data processing building blocks

among Europe’s space equipment suppliers

astrium satellites central engineering – dependability, data processing and software division...

Documents

mbps data

seminar high speed data

compressed data hrsc

serial data link

spacewire links slide

seminar esa missions

discrete links

software division asg7