Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 1
Highly Integrated Payload Suites and Related Data Link Requirements
P. Falkner, C. Erd
Science Payload & Advanced Concepts Office
ESA - ESTEC
[email protected] Exploration Studies
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 2
1. Background
•Technology Reference Missions (TRM’s)MotivationMissions (TRM’s)
• BepiColombo and Solar OrbiterPayload Suites
2. Application
• Highly Integrated Payload Suites
=> Requirements for Data/Command Links
3. Conclusion
Overview
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 3
Technology Reference Missions (TRM)
• Strategic focus on critical technology developments for potential future science missions
• Study technologically demanding, science driven missions that are not part of the science program
�� Identifying Identifying critical technologiescritical technologies to enable future missionsto enable future missions
�� Establishing a Establishing a roadmaproadmap for technology developmentsfor technology developments
�� Enable Enable low resource low resource exploration missionsexploration missions
! Enable new “low-cost” science missions at increased frequency
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 4
Current TRMs:Current TRMs:
�� Solar Polar OrbiterSolar Polar Orbiter
�� Deimos Sample Return� Venus Entry Probe� Jovian Explorer� Interstellar Heliopause Probe
�� Atomic InterferometerAtomic Interferometer�� XX--ray Interferometerray Interferometer�� Gamma Ray ImagerGamma Ray Imager
Technology Reference Missions
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 5
Technology Reference Missions
• Use of MicroSats (200 kg class)
� Smaller launcher, lower cost - typical Soyuz-Fregat class
� More frequent (phased approaches)
� Based on Highly Integrated Payload Suites
� Use of Centralised Processing and Power Supply Systems
� Require resource reduction(Payload and S/C-subsystems)
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 6
Venus Entry Probe - TRMDetailed study of Venus lower atmosphere (physics, chemistry and exobiology)
• Origin and evolution of Venus atmosphere→ Comparative planetology
• Composition of lower atmosphere→ Atmospheric chemistry→ Greenhouse effect→ Tracking active volcanism
• Atmospheric dynamics→ Super-rotation→ Hadley cell circulation?
• Aerosol analysis/Exobiology→ Analysis of large cloud particles
! Low resource spacecraftLow resource spacecraftLow resource spacecraftLow resource spacecraft
! Highly integrated remote sensing payloadsHighly integrated remote sensing payloadsHighly integrated remote sensing payloadsHighly integrated remote sensing payloads
! Atmospheric entry of a microAtmospheric entry of a microAtmospheric entry of a microAtmospheric entry of a micro----aerobotaerobotaerobotaerobot
! MicroMicroMicroMicro----aerobot suitable for Venus atmosphereaerobot suitable for Venus atmosphereaerobot suitable for Venus atmosphereaerobot suitable for Venus atmosphere
! Miniaturized payload for inMiniaturized payload for inMiniaturized payload for inMiniaturized payload for in----situ atmospheric measurementssitu atmospheric measurementssitu atmospheric measurementssitu atmospheric measurements
! Atmospheric microprobesAtmospheric microprobesAtmospheric microprobesAtmospheric microprobes
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 7
Deimos Sample Return - TRM
! Obtain material from a D-class asteroid
! Sample will contain 10% of Mars material
! Mission Heritage can be used for future Small Body Sample Return Missions
! Direct Earth Re-Entry
! Main P/L:Sampling Device & Supporting Instruments(cameras, imaging spectrometer, lidar, laser altimeter)
! Sample Mechanism, Rendezvous Technology, re-entry
Projectile Impact coupled with Cone Shaped Collector (as designed for MUSES-C)
DeimosSampleReturn
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 8
The Jupiter Microsat Explorer - TRMStudy the Jovian environment (e.g. radiation, magnetic field)
& Investigate Jovian Moons, especially Europa:
� study the global topography� study the composition of the (sub)surface
� Development of low resource MicroSats� Planetary protection compatible systems
� Development of highly integrated systems� Maximise the use of solar power, even at 5 AU from Sun
� Low power / low mass deep space communication� Surviving deep space as well as Jupiter�s extreme radiation environment
� mapping of the ice thickness� is a subsurface ocean present ?
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 9
Interstellar Heliopause Probe - TRM
Explore and Investigate the Interface between the Local Interstellar Medium and the Heliosphere
Scientific questions to be answered:
� What is the nature of the interstellar medium?
� How does the interstellar medium affect the solar system?
� How does the solar system impact the interstellar medium?
� What are the clues to the solar system origin in the outersolar system?
Requirements:
� Reach 200 AU in 25 years in direction of Heliopause nose
� Soyuz-Fregat SF-2B launch vehicle
� enabling Technologies for outer Planets (Saturn, Uranus, Neptune, Pluto)
� Communication up to 200 AU with a data rate ~ 200 bps
� Highly autonomous spacecraft with a lifetime > 25 years
� Design of a capable low-resource, low mass payload
� Propulsion system delivering S/C to 200 AU within < 25 years
� Power system at 200 AU with a lifetime > 25 years
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 10
Solar Orbiter (SOLO)
-1.5
-1
-0.5
0
0.5
1
-1.5 -1 -0.5 0 0.5 1 1.5
X [AU]
Y [
AU
]
Satellite
Earth
thrust
Venus
Solar Orbiter will, for the first time:� Explore the uncharted innermost regions of our solar system
� Study the Sun from close-up (45 solar radii)
� Fly by the Sun tuned to its rotation and examine the solar surfaceand the space above from a co-rotating vantage point
� Provide images of the Sun�s polar regions from heliographic latitudes in excess of 30°
Solar Orbiter Challenges:Heat load: up to 34 kWm-2 (25 solar constants), variableRadiation environment affects:
• Detectors• Electronics• Optical coatings and filters
Limited spacecraft resources: mass, power, telemetry
⇒ Develop smart and low-resource instrumentation
⇒ Target and initiate new technology developments
⇒ Study critical payload and spacecraft issues
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 11
BepiColombo1. Origin and evolution of a planet close to the parent star2. Mercury as a planet
form, interior, structure, geology, composition, craters3. Mercury�s vestigial atmosphere (exosphere):
composition and dynamics4. Mercury�s magnetized envelope (magnetosphere):
structure and dynamics5. Origin of Mercury’s magnetic field6. Test of Einstein’s theory of general relativity
(Detection of potentially Earth-threatening asteroids)
Three Scientific Elements
Mercury Planetary Orbiter (MPO)Mercury Magnetospheric Orbiter (MMO, ISAS provided)Mercury Surface Element (MSE)
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 12
Highly Integrated Payload Suites
=> data link/ command link top level requirements
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 13
Highly Integrated Payload Suite (HIPS)
Physical Front EndsPhysical Front EndsDetectors, Optics,..Detectors, Optics,..
Data HandlingData Handling
�� Data ProcessingData Processing�� Front End ControlFront End Control�� HousekeepingHousekeeping
�� FPGAFPGA�� multiple DSP multiple DSP �� µµCC��ss
Front End Front End ElectronicElectronic
Front End Front End ElectronicElectronic
Front End Front End ElectronicElectronic
��
S/C interfaceS/C interface
�� DC/DC converterDC/DC converter�� Data I/OData I/O�� CommandingCommanding
Instrument SuiteInstrument Suite
Collection of InstrumentsCollection of Instruments
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 14
DPU 1
DPU 2
Mass Memory
EPROM SRAM PROM
EPROM SRAM PROM
DH&Cinterface
DH&Cinterface
Instrument Controller
Instrument Front End Electornics
InstrumentInterfaces
High Resolution and Stereo Camera
InstrumentInterfaces
Instrument Controller
Instrument Front End Electornics
Instrument Controller
Instrument Front End Electornics
Gamma-Ray/Neutron Spectrometer
Instrument Controller
Instrument Front End Electornics
Radiometric IR Mapping Spectrometer
VIS-NearInfrared Spectrometer
Instrument Controller
Instrument Front End Electornics
Laser Altimeter
Optics
Optics
Optics
Optics
Detector
Detector
Detector
DetectorS C HICDHS
Laseretc.
Principle Block Diagram
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 15
Instrument Controller
DPU interface1
S-Wire
DPU interface2
CAN
Latch-Upcontroller
Memory Interface
external local
Memory
Local Houskeeping
Controler
Local Processing
Unit
Instrument Controller
optinal external Compressor
Hardware Controller
OptionalTest interface
Detector ReadoutControl
Voltages
Currents
Controls
Parameters
MUX
ADC
Instrument Controller Unit (FPGA based)
`
Detector (Focal Plane)
ADC
Optics
DAC
Read Out
Possibly ASICbased
Read-Out
Data&
Command
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 16
Instrument controller Instrument controller FPGA basedFPGA based
Stereo / Solar Electron and Proton TelescopeStereo / Solar Electron and Proton Telescope
Instrument Controller - Example
Stereo SEPT Instrument Controller, P.Falkner 2001Stereo SEPT Instrument Controller, P.Falkner 2001
FPGAFPGASRAMSRAM
CrystalCrystal
DACDAC
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 17
Complete Block Diagram
FPGA Xilinx Qpro Virtex
FillFactoryIBIS 5
79LV0832 EEPROM
48SD1616 SRAM
9042ADC
12bits
Auto WhiteBalancing
Auto ExposureControl
CorrelatedDouble Sampling
Auto Black Calibration
H SHIFT REGISTER
V
SHIFT
REGC1 W
Sync
O2
C2
O1
FPGA Xilinx Qpro Virtex
Time Sync
X Amp
Y Amp
V
SHIFT
REG
H SHIFT REGISTER
High Voltage Unit
48SD1616 SRAM
79LV0832 EEPROM
Temp Ctrl
Cover Ctrl
MCP RoentDek DLD
9042ADC 12 Bits
9042ADC 12 Bits
UVSHRC
9042ADC 12 Bits
Timing Generation
Bias Corrector
ROW
MUX
BiasCtrl
&
TimeCircuit Colomn Amplifier
Colomn MultiplexerOutamp
ReadOut CellsuBolometer
Sofradir ID ML 073
Data Register Load Circuit
Correction Coefficient Memory
XenicsXFPANIR
H SHIFT REGISTER
V
SHIFT
REG 9042
ADC 12 Bits
R-IMS
VN-IMS Detector Array +Preamps
Amp
Amp
Peak Hold Multiplexer
RC Filter +
Sum
9042 ADC 12
Bits
Fast Discrimina
tor
Discriminator
Temp Ctrl
MXS
Single Pixel Detector 1+
PreampAmp Peak Hold
RC Filter
9042 ADC 12
Bits
Fast Discrimina
tor
Discriminator
Temp Ctrl
Single Pixel Detector 2+
Preamp
MUX
SXM
Laser Source
DetectorAmp
Pulse Peak, width & energycounters
Filter
9042 ADC 12
Bits
Discriminator
Noise Counter
Temp Ctrl
Time Intern
alUnit
HVU
LAT
Amp
AmpShaper
Disc
Disc
Shaper
Time pick Off
MUX
Pile Up Reject
Logic
ADC
S/H
Sensor Array
MGNS
FPGA Xilinx Qpro Virtex
L-CamSensorArray
79LV0832 EEPROM
48SD1616 SRAM
9042ADC
12bits
Auto WhiteBalancing
Auto ExposureControl
CorrelatedDouble Sampling
Auto Black Calibration
H SHIFT REGISTER
V
SHIFT
REG
Sync
S-CamSensorArray
H SHIFT REGISTER
V
SHIFT
REG
9042ADC
12bits
S-CAML-CAM
RSE MAG
Acache
SecIRQ
CPUExternalPROM
CPUExternalMemory
FPUMEIKO
Dcache 32Kbits Icache 32Kbits
Spark V8 CPU
RAM Ctrl
PCI MasterTarget
PCI WrapperMaster/Slave
8x328x32
CPU AHB Arbiter Decoder
AHB/APBBridge
IO I/F
IRQ TIMERs WDOG UARTs
HurriCAN
CAN Open Manager
Encoder
Encoder
FIFO
FIFO
State Machine (FPGA)N.3
SpacewireI/F
CAN I/F
To PCIBUS
To FPGA To FPGA
To FPGA
To FPGA
To FPGA
To FPGA
To FPGA
To FPGA
To FPGA
FPGA Xilinx Qpro Virtex
Time Sync
X Amp
Y Amp
V
SHIFT
REG
H SHIFT REGISTER
High Voltage Unit
48SD1616 SRAM
79LV0832 EEPROM
Chopper Ctrl
2D MCP RoentDek DLD
9042ADC 12 Bits
To
CAN
MUX
Filter
Internal Time Unit
MUX
NPA STROFIO
FPGA Xilinx Qpro Virtex
Time Sync
X Amp
Y Amp
High Volta
ge Unit
48SD1616 SRAM
79LV0832 EEPROM
Chopper Ctrl 9042
ADC 12 Bits
To
CAN
MUX
Filter
Internal Time Unit
MUX
NPA ELENA
Discriminator
Used for analysis and optimization of the integrated instrument Used for analysis and optimization of the integrated instrument suitesuiteCourtesy of Cosine B.V. Courtesy of Cosine B.V.
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 18
Highly Integrated Payload Suites / TM- rates
Mission P/L Mass Range (kg) Data Rate
Solar Orbiter < 150 75 kps (750 kbps max)BepiColombo - MPO 40 - 50 ~ 60 kbpsDeimos Sample Return (TRM) 10 - 20 10 kbpsVenus Entry Probe - Relay Sat (TRM) 20 ~ 50 kbpsVenus Entry Probe - Orbiter (TRM) 10 - 20 50 kbpsJupiter Explorer (TRM) 20 ~ 50 kbpsInterstellar Heliopause Probe (TRM) 20 - 40 200 bpsAerobot 5 1 kbpsMicroProbes 0.01 - 1 100 bps
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 19
BC/MPO – HIPS present model P/L
(kg) (W) (Mbps) (kbps) (kbps)
Nr. Instruments Mass Power Peak Rate
Data Rate uncompr.
Data Rate compr.
1 High Resolution Colour Camera HRC 1.10 1 34.0 85.5 6.02 Stereo Camera S-CAM 0.55 1 2.5 37.9 2.73 Limb Camera L-CAM 0.34 1 0.6 4.2 0.34 Visible Near Infrared Mapping Spectrometer VN-IMS 0.80 7 1.7 21.6 7.25 Radiometric Infrared Mapping Spectrometer R-IMS 2.20 3 1.9 33.5 6.76 Ultraviolet and Visible Spectrometer (UVS) UVS 1.65 2 0.20 1.7 1.17 Mercury X-ray Spectrometer / Solar x-ray Monitors MXS/SXM 2.10 5 0.04 13.2 6.68 Mercury γ-ray Spectrometer MGNS 3.00 3 1.6 1.6 1.69 Laser Altimeter LAT 5.53 (20) NA 0.14 0.1
12 Neutral Particle Analyzer NPA 1.80 3 0.014 3.2 1.010 Radio Science Experiment RSE 6.70 10.6 <<< 0.1 0.111 Magentometer MAG 4.15 2 0.004 0.1 0.113 Platform 3.00 014 Dual Central Processing Unit 2CPU 3.00 2015 Central Payload Power Supply CPPS 0.70 11.716 Harness 1.68
Subtotal 38.3 70.3 202.7 33.5Contingency 7.7 14.1
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 20
Highly Integrated Payload Suites
• FPGA’s and ASICS (e.g.) contain instrument controller + data link/commanding interfaces
• Strong interest to reduce part count -> keep PCB small,manufacturing and testing simple.
• Space Wire as high data rate link > 1 Mbps(standard requires ~ 5000 gates = % range)
• CAN bus as low data rate link < 1Mbps(6.5% of Actel RTAX-1000)
• Low resource need allows implementation of both controllers into single FPGA including Transceiver, Interface and the Instrument Controller
• Driver is the data link(command link low data rates, except instrument FE configuration)
Courtesy of Cosine B.V. Courtesy of Cosine B.V.
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 21
Highly Integrated Payload Suites - Implementation
• Next Step = Implementation into Bread Boardstudy data flows & potential conflicts
• Use of simulators and instrument Bread Boards
• Main CPU’s possibly implemented in rad-hard FPGA’s(e.g. ACTEL RTAX 1000/2000)
HIPS
Simulator
SpaceWireInterface
CAN BusInterface
InstrumentFront End
SpaceCraftInterface
InstrumentFront End
InstrumentSimulator
InstrumentFront End
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 22
Conclusion
• HIPS require medium and high speed links (CAN & S-Wire)
• VHDL based implementation of transceiver and controllerinto FPGA and ASIC’s
• For small distances: use of FPGA I/O levels (e.g. LVDS support by Actel -> reduces need for additional drivers)
• Precise time stamping required (ms range)
• PC based equipment needed for test/development phasealready available
• All doable – no showstopper => start to implement into Bread Board
• Potential need for support by specialists -> motivation of this talk
Science Payload & Advanced Concepts Office
International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A
Page 23
References
[1] Julian Harris (Swiss Space Technology), Study of the use of[1] Julian Harris (Swiss Space Technology), Study of the use of FPGA technologies in a highly FPGA technologies in a highly integrated payload suite, Ref SSTintegrated payload suite, Ref SST--HCHC--TNTN--001, October 2003001, October 2003
[2] C. Erd et.al., BepiColombo Payload Definition Document (PDD[2] C. Erd et.al., BepiColombo Payload Definition Document (PDD) 3.1.1, 30 June 2003, ) 3.1.1, 30 June 2003, ref: SCIref: SCI--A2002/007/Dc/CE,Cr_BC_TN15A2002/007/Dc/CE,Cr_BC_TN15
[3] P. Falkner, Science Future Programme Technologies, Workshop[3] P. Falkner, Science Future Programme Technologies, Workshop on Spacecraft Data Systems, 5.on Spacecraft Data Systems, 5.--7. 7. May 2003 @ ESTECMay 2003 @ ESTEC
[4] [4] M. Collon, J. M. Collon, J. MontellaMontella, S. Kraft (cosine Research B.V.),, S. Kraft (cosine Research B.V.), Highly Integrated Payload Suites (HIPS)Highly Integrated Payload Suites (HIPS)Concept Study, 5Concept Study, 5thth IAA conference on low cost Space MissionsIAA conference on low cost Space Missions
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