Highly Integrated Payload Suites and Related Data Link...

Science Payload & Advanced Concepts Office

International SpaceWire Seminar 2003 ESTEC, 4-5. November, P. Falkner, SCI-A

Highly Integrated Payload Suites and Related Data Link Requirements

P. Falkner, C. Erd


ESA - ESTEC

[email protected] Exploration Studies



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



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



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



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)



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



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



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 ?



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



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



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)



Highly Integrated Payload Suites

=> data link/ command link top level requirements



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



��

S/C interfaceS/C interface

�� DC/DC converterDC/DC converter�� Data I/OData I/O�� CommandingCommanding

Instrument SuiteInstrument Suite

Collection of InstrumentsCollection of Instruments



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





Gamma-Ray/Neutron Spectrometer



Radiometric IR Mapping Spectrometer

VIS-NearInfrared Spectrometer



Laser Altimeter

Optics

Optics

Optics

Optics

Detector

Detector

Detector

DetectorS C HICDHS

Laseretc.

Principle Block Diagram




DPU interface1

S-Wire

DPU interface2

CAN

Latch-Upcontroller

Memory Interface

external local

Memory

Local Houskeeping

Controler

Local Processing

Unit


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



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



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


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


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


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


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.



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



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



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.



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



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



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

-- END END --

Highly Integrated Payload Suites and Related Data Link...

Documents

Transcript of Highly Integrated Payload Suites and Related Data Link...