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The AEOLUS Mission
- Upcoming satellite level industrial activities
ADM-Aeolus CAL/VAL Workshop, ESRIN
Richard Wimmer, Airbus Defence and Space Ltd, UK
10th February 2015
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ADM-Aeolus Overview
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
2
Mission Objectives
• To measure global wind profiles up to an altitude of 30km
Mission Details
• Duration: 3 years plus 3 month commissioning phase
Mission Orbit
• Sun-synchronous, dusk/dawn orbit
• Inclination 97°
• Altitude: 408km
Configuration
• Total dry mass of 1090kg comprising:
• Platform 614kg (plus 264kg propellant)
• Payload 476kg
• Dimensions (launch configuration)
• height 4.37m, length 2.08m, width 2.00m
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Aeolus Electrical architecture
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
3
Switched
supplies
50V Bus
Switched
supplies
28V Bus
Test
TTC uplink & downlink
Command and monitor
MIL 1553 data bus
Mass memory
Processor
Dedicated interface
modules
Command and Data
Management Unit (CDMU)
Solar arrays
(SA)
Heaters –
Software
controlled
Heaters –
Thermostat
controlled
Thermal control
Power control and
distribution unit
(PCDU)Battery
(BAT)
Aladin Control
and Data
Management
Unit (ACDM)
Transmitter Laser
Electronics (TLE)
Detection Electronics
Units (DEU)
Temperature
sensors
Thermal Hardware
Mechanisms
ALADIN Instrument
Umbilical
Coarse Earth Sun Sensor (CESS)
Inertial
Measurement
Unit (IMU)
GPS
Star Tracker
(AST)
Magnetometer
(MTM)
Magnetorquer
(MTQ)
Reaction
Wheels
(RWU)
Rate
Measurement
Unit (RMU)
Command,
monitor and
synchronisation
X-Band Modulator
and Transmitter
S-Band Transponder
and RF Distribution
Electrical Power Subsystem
(EPS)
X-band
science
downlink
S-band TTC
link
Science data
AOCS interfaces
Thermistor
interfaces
Attitude and Orbit Control
Subsystem (AOCS)
Non-redundant
Hot or cold
redundant
Science data
50V
power
bus
28V
power
bus
Propulsion subsystem
PT
LV LV
Propulsion
interfaces
RF communications
subsystem
Heater
supplies
RFsw/Filter
RF hybrid1553RT
1553RT
1553BC
PT
Tanks
UART
Separation
(via Umb)
1553RT
1553RT
1553RT
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Aladin Instrument Functional Block Diagram
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
4
Telescope
T/R Diplexer
& Relay Optics
Laser Heads
(RLH & PLH)
Laser
Thermal
Control
Mie & Rayleigh
spectrometers
DFU1 DFU2
Detection Electr.
Unit (DEU)
Aladin Control and
Data Management
unit (ACDM)
Transmitter Laser
Electronic (TLE)
Chopper
mechanism
Flip-flop
mechanism
InstrumentCore
ElectricalPanel
Structure
& Thermal
ControlMech/therm.
IF to PFHeaters
Mech/therm.
IF to PF
TM/TC
bus
Reg.
Power
Reg.
Power
Transmitted
beam
Received
beam
Science
Data
TxA
I/F with
S/L
Thermistors
Reg.
Power
Unreg.
Power
Detection
PCDU CDMU
AL
AD
IN
Unreg.
Power
Survival
Survival
Pressure
IF to PF
ICS
ICS
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Aladin Instrument Optical Bench Assembly
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
5
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Project Industrial Organisation
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
6
Prime Airbus Defence and Space, UK
Aladin Instrument Airbus Defence and Space, F
Laser Transmitter Selex-ES, I
Aladin Control & Data Management
Syderal, CH
Detection Electronics Patria, Fin
Spectrometers RUAG, CH
Aeolus Platform Airbus Defence and Space, UK
In-Situ Cleaning System
On-Board Software Scisys, UK
Solar Array Airbus Defence and Space, NL
Satellite AIT Airbus Defence and Space, UK
Central Checkout System
Airbus Defence and Space, D
Test Facilities ETS & CSL
Ground Segment L1b Processor
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Aeolus Satellite Configuration
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
7
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Aeolus Satellite - Aladin Instrument
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
8
Main telescope assembly
Mie spectrometer
Transmit/Receive Optics
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Aeolus Satellite - Aladin Instrument
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
9
Laser Transmitter – lower optical bench
PLH
ACDM
RLH
TLE
Combined flight laser and OBA test set-up
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Aeolus Satellite - Aladin Instrument
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
10
Main structure including telescope and baffle Laser Cooling System
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10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
11
Aeolus In-Situ Cleaning Subsystem Panel
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10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
12
Aeolus Satellite - Flight platform with Aladin OSTM
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to
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ou
t th
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Aeolus Satellite - Flight platform with Aladin OSTM
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
13
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mm
un
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to
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ith
ou
t th
e o
wn
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Project Status
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
14
Aeolus KO 2002
• Prime: Airbus DS, UK, Instrument: (Aladin) Airbus DS, F, Electrical Systems: Airbus DS, D
Satellite level CDR and StM EVT campaign completed in 2005
• Flight structure with equipment mass dummies
• Aladin OSTM mechanical, thermal and optical tests completed
Aladin delayed due to laser technology problems
Aeolus flight platform integration and testing completed in 2009.
• Platform Qualification Review successfully completed in November 2009
Platform in storage at Stevenage since early 2010 awaiting Aladin instrument.
• Routine maintenance and implementation of Oxygen purge system (ICS)
New ‘VESTA fairing’ shock test for VEGA launcher in 2013
• EMC testing of platform to prove compatibility with launcher
Instrument delivery 2015
QR/FAR end 2016
Launch on VEGA (back up Eurockot)
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t th
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Laser Transmitter Technology Challenges
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
15
Aladin laser transmitter development has been significantly more challenging than anticipated with various delays
caused by technology development issues and major test anomalies with consequent recovery actions and
improvements:
Nov ‘06: mirror mounts in-stability new mirror mount technology
Jan ‘08: master oscillator pre-lasing in vacuum new polariser
Apr ;08: LID in master oscillator components change of damage margin requirements and optics
Apr ‘08: IR beam shift air/vacuum amplifier couplings modified
Dec ‘08: LIC on UV optics in-situ cleaning system introduced (O2 purge) and optics change
Sept ‘09: Long term UV energy drift amplifier coupling interface modified
May ‘10: LID in master oscillator de-rate MO energy to 5mJ
Mar ‘12: LID on UV optics IR beam expansion, crystal optimisation, stronger UV coatings
Mar ‘13: Successful endurance test in air ‘GO’ for laser qualification, screen all flight optics
Aug ‘13: Successful endurance test in vacuum (operational qualification)
Dec ‘13: Laser non-operational qualification (mechanical and thermal)
Jan ‘14: Delivery of 1st flight laser to Airbus DS
Aug ‘14: Successful testing of Aladin Optical Bench Assembly with flight laser
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ou
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Key validation tests remaining
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
16
Instrument Functional Performance Tests (IFP) Aladin level
• Prime and Redundant lasers emitting via S-TRO to OGSE. OGSE simulated atmospheric return signal to
detection chain.
Aladin EMC test
• Conducted emissions and susceptibility
Aladin Functional Health check
• TM/TC and data interface reference checks with Laser off
System level performance tests (IST & SVT)
• Test of platform and Aladin together with a typical mission timeline. SVT 1 with ESOC
System functional test (SFT)
• Subset of IST to check integrity between mechanical tests
Satellite vibration, acoustic and shock tests
• Mechanical launch environment with SFT performed to demonstrate spacecraft capability
Satellite Thermal Vacuum Test (Tvac)
• Operational environment with Aladin operating via OGSE (like IFP). Laser at full power.
Satellite EMC test
• Auto compatibility
Final functional tests
• Including repeat of Aladin Health check
……Launch and IOC!!
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to
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ith
ou
t th
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Aeolus Satellite - AIT flow
10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
17
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an
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ll n
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be
co
mm
un
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ted
to
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hir
d p
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y w
ith
ou
t th
e o
wn
er’
s w
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10th February 2015
ADM-Aeolus CAL/VAL Workshop, ESRIN
18
Thank you for you attention…
…any questions?
