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Vegetation Research and Detection
Small Satellite Project 2011/2012
Elisabete Dias, Victor Hocke, Andreas Hornig, Nicolay Kbler, Mark Ltzner
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Agenda
1. Mission
2. Payload
3. Orbit
4. Subsystems
Structure / Thermal
Power System
Attitude Control System
Onboard Data Handling
Communications
5. System Budgets
University of
the Azores
University of
Stuttgart
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Mission
Mission Definition
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Payload
Subcontractor
Berlin Space Technologies 6 spectral bands
near infrared, blue, yellow, green, red, red edge
GSD < 10 m (nadir)
Swath width100 km @ 600 km
MTF > 0.12
Favorable SNR
Mass < 20 kg
Power < 60 W(Target: 30 W)
Dimensions450 x 285 x 120 mm
Development time
18 - 24 month
Facts
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Payload
Continuous strip
SNR: 70 75
Permanent nadir orientation
Single scenes
Forward Motion Compensation (4:1)
Increased dwell time
SNR > 100
Requires detailed target planning
2 backup observation possibilities
Scan Mode Scene Mode
Operation Modes
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Orbit
Orbit Requirements
Full coverage of the Archipelago ofthe Azores
Constant lighting conditions
Max. 25 years
(space debris mitigationMin. 2 years (design lifetime)
Short revisit time
Low altitude
(for higher resolution)
1200 AZOT
Possible Orbits
Sun synchronous
Altitude / LTAN tbd
Lifetime and resolution limitaltitude to 500 600 km
Orbit Decay
10 40 km (solar activities)
Project
Mass AreaInitialaltitude
decay (2 years)
BIRD 94 kg 1,1 m2 565 km 27 km
SNOE 115 kg 0,9 m2 556 km 15 km
Orbit Design
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Orbit
Chosen swath width:95 km @ 575 km
Ground track distance:
93 km @ 575 km 2 km overlap
11:34 LTAN
7 consecutive observations,waiting time: 16 days
Orbit Design
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Structure / Thermal
Secondary Requirements
Low cost
Minimal + Simple Harness
Simple Integration
Simple servicing
Low mass
Stability of line of Sight (Camera stability)
Mandatory Requirements
Accesibillity of all Electronics
Eigenfrequency
Thermal Control
Quasistatic Loads must be withstood Dimensions must not exceed 600 mm x
700 mm x 850 mm (PSLV requirement)
Structure
Options
OptionsFEM check
Options
Trade off
Complete
FEM check
Detailed
construction
Structure
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Structure / Thermal
Barrel
Cube
Hexagon
Aluminium barrel Structure
Mass: ca. 110 kg
Hybrid Aluminum/Composite
Mass: ca. 110 kg
Hybrid Aluminum/Composite
Mass: ca. 100 kg
Options Trade-off
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Structure / Thermal
Weight Hexagon Cube Barrel
Mass 2 4 2 2
Cost 1 2 3 2
Stability ofline of sight
2 3 5 5
Thermalcontrol 1 2 5 5
Harness 1 5 2 2
Integration 1 5 2 2
28 26 25
Hexagon Cube Barrel
1. Lateral EF[Hz]
77 136 59.9
2. Vertical EF[Hz]
231 304 266
1. Lateral Mode
FEM Check
Options Trade-off
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Structure / Thermal
765mm
I-DEAS ModellCAD Modell
Complete FEMcheck
Structure
Lock System
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Structure / Thermal
Detailed FEM check
Lateral1. eigenfreq. [Hz] 77
2. eigenfreq. [Hz] 120
3. eigenfreq. [Hz] 138
4. eigenfreq. [Hz] 156
Vertical
1. eigenfreq. [Hz] 231
Min eigenfreq. lateral: 45 Hz
Min eigenfreq. vertical: 90 Hz
1. Lateral Mode1. Longitudinal Mode
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Structure / Thermal
Max. Stress[N/mm] Max. Strain
X Direction 133 0,49*10-4
Y Direction 120 0,52*10-4
Z Direction 29.5 0,94*10-4
Aluminum Stress Composite Strain
Krit.
Krit.
Krit.
Max. Strain: 10-4
Max. Stress: 150 N/mm
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Detailed FEM check
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2
1
3
4
5
6
7
8
9
3
1
22
21
1
Component Placement
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Structure / Thermal
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Structure / Thermal
Cable support
Large Volume
for Harness
Detailed Construction
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Integration Procedure
Structure / Thermal
Step 1- AluminumStructure
Step 2- IntegrationPlatform
Step 4 - Solar PanelsStep 3- CompositeStructure
Simple Testing ofcomponents
Simple Integration
of Harness
Flight mode Integration of
Solar panels
Transport mode Integration of
Composite structure
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Structure / Thermal
Deployment Mechanism 6 x GFK brackets
Launch
Position
Deployed
Position
Detailed Construction
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Structure / Thermal
Orange: Primary heat conducting structure
Red: Radiators
Multilayer Insulation
Aluminum heat conducting plates are
fixed to the Composite by floating inserts
Line of Sight is highly incensitive to
thermal strain
High Power Electrical Components are
placed on the service plate(Battery/PCDU/OBC/COM Equip.)
Heater (critical components, e.g. Battery)
Thermal control:
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Structure / Thermal
Thermal Simulation
164 Thermal Knots
ComponentDissipated Energy
[W] (Hot Case)Dissipated Energy[W] (Cold Case)
OBC 10 10
MMU 15 5
RIU 5 5Batteries 5 5
PLC 10 -
PCDU 10 10TMTC 2 2
RW 7 7
Hot Case Radiator Area: 0.25 m2
Cold Case Heater Power: 15 W
Temperature Limits
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Structure / Thermal
Thermal Simulation: Maximum thermal loads (hot case)
Solar
Arrays
Battery
averaged Temp.
Payload
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Structure / Thermal
Thermal Simulation: Minimum thermal loads (cold case)
Solar
Arrays
Battery
averaged Temp.
Payload
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Electrical Power System
PCDU
Battery Cells
Load BalancerHeater
SolarPanels
B1 B2 B3 P2P1
System
SolarPanel
BatteryP
ack
EPS Overview
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Electrical Power System
0 10 20 30 40 50 60 70 80 90 100
0
50
100
150
200
250
300
350
400
Solar Power 5
P average 5
B1 B2 B3 P2P1Solar
Panel
Solar Panels
Solar power Failure Scenario
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Orbitrun [%]Power[W]
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Electrical Power System
0 10 20 30 40 50 60 70 80 90 100
0
50
100
150
200
250
300
350
400
Solar Power 5
P average 5
0 10 20 30 40 50 60 70 80 90 100
0
50
100
150
200
250
300
350
400
Solar Power 5
Solar Power 4
P average 5
P average 4
Solar Input
System Power
Decrease in:
Design Power 120W
B1 B2 B3 P2P1Solar
Panel
Solar Panels
Solar power Failure Scenario
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Orbitrun [%]Power[W]
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Electrical Power System
0 10 20 30 40 50 60 70 80 90 100
0
50
100
150
200
250
300
350
400
Solar Power 5
P average 5
0 10 20 30 40 50 60 70 80 90 100
0
50
100
150
200
250
300
350
400
Solar Power 5
Solar Power 4
P average 5
P average 4
0 10 20 30 40 50 60 70 80 90 100
0
50
100
150
200
250
300
350
400
Solar Power 5
All Systems
Solar Power 4
P average 5P average 4
B1 B2 B3 P2P1Solar
Panel
Solar Panels
Above System Power
new system
power level
Solar power Failure Scenario
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Orbitrun [%]Power[W]
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0 10 20 30 40 50 60 70 80 90 100
0
20
40
60
80
100
120
140
160
180
Power Consumption during Worst Case Orbit
Power vs. Orbitrun
All Systems
All Systems avg
payload
com
acstherm
obdh
pow
orbitrun [%]
power[w
]
Electrical Power System
High DatarateCommunication
COM1
Observation
Heater
Standard DatarateCommunication
COM2 & COM3
High DatarateCommunication
COM1
Power Consumptionduring Worst Case Orbit
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Electrical Power System
+ Injection Mode
Standard Modes
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Electrical Power System
Solar Panel Trade off
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1st Layer
Optimized pattern with 80mm x 40mm (93%)
13 x 7 Cells per panel
Electrical Power System
300mm
8
00mm
Vs.
Solar panel (layer) design
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1st Layer
Optimized pattern with 80mm x 40mm (93%)
13 x 7 Cells per panel
13 cells in series for nominal Voltage 28 V
Electrical Power System
Vs.
Solar panel (layer) design
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1st Layer
Optimized pattern with 80mm x 40mm (93%)
13 x 7 Cells per panel
13 cells in series for nominal Voltage 28 V
2nd LayerSeries connection on panel
Electrical Power System
Vs.
Solar panel (layer) design
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1st Layer
Optimized pattern with 80mm x 40mm (93%)
13 x 7 Cells per panel
13 cells in series for nominal Voltage 28 V
2nd LayerSeries connection on panel
3rd Layer
Parallel connection in panel sandwichFor capacity leverage to
Multiple interfaces to EPS system
Shunt System included
Electrical Power System
34
Vs.
Solar panel (layer) design
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Electrical Power System
Battery trade-off
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Electrical Power System
Solar PanelArea usage = 0,93Efficiency = 0,3Degradation = 0,03 1/a
Battery
C/d cycles = 60000
DoD = 20 %Degradation = 0,05 1/a
ACS
Solar angle accuracy = 2,5CommandsCOM-turns (2x) = 45 a 15minForwardMC = 45 a 1min
Solar Environment
Solar Constant= 1370 W/m^2
System
e_daylight = 0,8e_eclipses = 0,85PowerConsumption = 95WTotal Power(20% margin) = 375W
Mission
Time = 2 aOrbit Period = 99 minDaylight = 64 %Eclipse = 36 %
Battery Specification
Energy:488 Wh
Capacity:23,2 Ah @ 21V
17,4 Ah @ 28V15,7 Ah @ 31V
System Power:160 WBoosting Level
Battery Design Criteria
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Electrical Power System
0 10 20 30 40 50 60 70 80 90 100
0
20
40
60
80
100
120
140
160
180
Orbit injection until full deployment
Power Consumtion vs. Full injection
All Systems
payload
com
acs
therm
obdh
pow
Solar System Power
orbit injection run [%]
power[w]
OrbitInjection
StepwiseActivation
Solar PanelDeployment
SystemCheck
InjectionFinished
StartingMission
CriticalPhase
Power ConsumptionDuring Injection Period
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Attitude Control System
Control
Navigation
S/C dynamics
Software (algorithms)
implemented on OBC
Actuator system
Reaction
Wheels
Magnetic
Torquer
Sensor system
Magneto-
meter
Star-
trackerIMU
Sun
Sensor
disturbances
control
commands torques
physicalstatesensor
measurem.
ground
commands
data
handling
Overview
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Attitude Control System
Definition:functional &
perfomance
requirements
Quantification:
disturbance
environment
System Design:architecture
componentselection &
sizing
Algorithm
Definition
Attitude estimation
(e.g. QUEST)
Controller design
(e.g. PID, H_infinity)
ACS Design Workflow
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Attitude Control System
The satellite has different ACS Modes:
1. Detumbling-Mode
2. Safe-Mode
3. Idle-Mode
4. Science-Modes:
4.1 Nadir-Pointing
4.2 Forward Motion Compensation
De-
tumbling
Safe-
Mode
Idle-
Mode
Science-
Modes
TC
TC
TC
FDIR
FDIRFDIR
AUTOTC
TC
AUTOTC TC
TC triggered by Telecommand
(Ground Station or Mission Time Line)
AUTO triggered by nom. condition
FDIR triggered by failure condition
Detumbling Safe Idle
Science
MGM x x x (x)
MGT x x x (x)STR x x
IMU x x
RW x x
SuS x x x x
ACS Modes
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Attitude Control System
Counter-rotation enlarges integration time
Rotation for FMC = 4
4x observation time constant pitch rate approx. 0.5/s
total rotation angle approx. 30
observation time approx. 1 Minute
Forward Motion Compensation
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Attitude Control System
2 Star Trackers
ST-100 (Berlin Space Technologies)
Accuracy: 200/30Star map included
2 Magnetometer (ZARM)
2 Inertial Measurement Units
Sensonor STIM210
MEMS-based 3-axis gyro module0.5/h bias instability, 0.10/h ARW
8 Sun Sensors (IRS)
Criteria Weight
SensonorSTIM210
LitefmuFORS-2
Cost 20% 3 2
ARW 25% 2 3
Bias 25% 3 2
Power 10% 3 2
Volume 10% 3 2
Mass 10% 3 2
Total 2,75 2,25
Sensor Concept
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Attitude Control System
3 Magnetic Torquers (ZARM)
two coils per unitLinear Dipole Moment 6 Am2
4 Reaction Wheels
(Astro- und Feinwerktechnik)
angular momentum: 0.1 Nms @ 5000 rpm
nominal torque: 0.005 Nm
tetrahedral configuration (redundancy)
Actuator Concept
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Attitude Control System
constrains:
shadowing effects (SuS, STR)
sun/earth blinding (STR)electromagnetic compatibility (MGM, MGT)
alignment
1. Reaction Wheels (RW)2. Sun Sensor (SuS)
3. Inertial Measurement Unit (IMU)
4. Star Tracker (STR)
5. Magnetometer (MGM)
6. Magnetic Torquer (MGT)
1
2
4 5
6
3
ACS Component Placement
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Onboard Data Handling
Onboard Data Handling
Tasks
Collect and process housekeeping data
Command attitude and thermal Control System
Store and process telecommands (CCSDS)
Send Data and Telemetry
ACS Attitude Control System
MMFU Mass Memory and Formatting Unit
OBC Onboard Computer
PCDU Power Control and Distribution Unit
PLC Payload ComputerRIU Remote I/O Unit
TCS Thermal Control System
TM/TC Telemetry/Telecommand
OBDH Configuration
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Supplier: Aeroflex Gaisler
RTEMS
Flight Heritage
MIL-Std 1553
Spacewire
89 DMIPS
Base Clock frequency 66 MHz
Supplier: SSTL
RTEMS
Flight Heritage
MIL-Std 1553
Spacewire
1800 DMIPS
Base Clock frequency 250 MHz
LEON3 UT699 IBM Power PC750 FL
Onboard Data Handling
Onboard Computer Trade-off
Not Rad hardenedCheaper Purchase and Testing
Rad hardenedexpensive purchase and testing
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Onboard Data Handling
Operating
System:RTEMS or others
Internal Memory:
265 MiBytes
2 MiBytes MRAM
16 MiBytes Flash
IBM PPC750FL
OBC Performance
COTS Flash Memory
Management Unit High Quality Product
Mass Memory and Formatting Unit
(+ Housekeeping
Data)
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Communication
COM3
COM2COM1
COM1 S-BAND TX High Data Mode, Payload Data
COM2 S-BAND TXRX of Telemetryand TX of Payload Data
COM3 L-BAND TXRX of Basic Telemetry
Tracking
Wakeup for Injection Phase
Power Mode Change
Communication System
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Communication
Horn
AntennaS-Band
COM1
OMT
CircularPolarization
D/AConverter
Modulator FrequencyMixer
Antenna13cm BandC
OM2
D/AConverter
Modulator FrequencyMixer
A/DConverter
De-Modulator
FrequencyMixer
Antenna23cm BandC
OM3
D/A
ConverterModulator
Frequency
Mixer
A/DConverter
De-Modulator
FrequencyMixer
Components
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Communication
IRS in-house manufactured
testing, validation and calibration campaigns (ex/internal)
hybrid COTS and space hardend components
Antenna Trade-off
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Communication
path link 0 and 90 elevation (2767 km / 575 km) output power drop from 1 W to 0,75 W
small changes atmospheric losses
Main Worst Case properties:
Link Budget (1)
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Communication
(ctd. 2nd Payload Constellation)
Link Budget (2)
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Communication
230mm60mm
Corrugated Horn
Circularly Polarization
Output Frequency2,4497 GHz
Antenna analysis (with TICRA Champ)
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Communication
IRS Groundstation
2,5 m parabolic antenna
S-Band (2,45GHz)
Gain 33 dB
Antenna analysis (with TICRA Grasp)
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Communication
SolarBank Angle = local time
SystemPower max = 40 WMMU = 200 GB
ACSPointing Accuracy = 2Attitude = 2
FrequenciesAmateur Radio Bands23cm, 13cm
PayloadMission Data = 30000 MBCompression(lossless) = 10%
MissionGroundstations = 2Visibility = 15minRevisit Time = 21 dMission Time = 7 d
COM SpecificationCOM1
2,44 GHz1200 kbit/s8FSK
EnvironmentPathlength best = 575 kmPathlength worst = 2770km
COM22,41 GHz2,43 GHz100 kbit/sQPSK8FSK
COM3
1,263 Ghz1,264 GHz10 kbit/sQPSK8FSK
Constellation1,2646 kbit/sQPSK
Design Criteria
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Communication
Global Volunteer Sensor Grid
Connected via the Internet
Amateur Radio Bands
Amateur Radio Operators and ordinary people
Global Sensor Grid
Tracking Data-Dump-Mode
Citizen Science & Crowd Communication
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Constellation Distributed Ground Stations
Communication
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Communication
CONTRA PRO
Global distribution of stations
Overall more contact time results to5% of COM1 datarate (1Mbit/s)
Cost efficient usage of frequency
No licencing of frequency band
No licences for operator
keeping amateur radio community happy
External tracking for orbit determination
Simple beacon and protocol design
Reduced communication
contact times per station
Only 6 kbit/s
Using amateur frequency
bands with smaller
bandwidth
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Constellation Distributed Ground Stations
System Budgets
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System Budgets
Mass Budget
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System Budgets
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System Budgets
VERDE Budget
Budget Relations in Respect to Hardware, Logistics & Working Hours
Satellite
Logistcs
Working Hours
VERDE Budget
Budget Relations in Respect to Components
Payload
COM
EPS
OBDH
ACS
STRUCTUR
THERMAL
Testing
Rest
Transport
Business Costs
Working Hours
Financial Budget
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Thank you!
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Thank you!
Thanks to all tutors at the Azores and in Stuttgart!
Questions?
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Contact
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Contact
VERDE Team
PayLoad: Elisabete DIAS
ACS & Orbit: Victor HOCKE COM & EPS & Constellation: Andreas HORNIG
OBDH & Thermal: Nicolay KBLER
Structure & Analysis: Mark LTZNER
Universities
University of Stuttgart www.uni-stuttgart.de Institute for Space Systems (IRS) www.irs.uni-stuttgart.de
Small Satellite Project www.kleinsatelliten.de
University of the Azores www.uac.pt
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Email:[email protected]
Facebook:http://on.fb.me/smallsatellitesazores
Sources
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8/2/2019 VERDE Small Satellite Project Uni Stuttgart Azores Presentation v5_c
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Sources
Companies
Berlin Space Technology www.berlin-space-tech.com
Azurspace www.azurspace.com
Emcore www.emcore.com
Saft Batteries www.saftbatteries.com
Point of Contact David REULIER
A123 Systems www.a123systems.com ZARM Technik www.zarm-technik.de
Sensonor www.sensonor.com
Astra- und Feinwerktechnik www.astrofein.com
Aeroflex Gaisler www.gaisler.com
Surrey Satellite Technology Limited www.sstl.co.uk
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(in order of appearance)
Sources
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8/2/2019 VERDE Small Satellite Project Uni Stuttgart Azores Presentation v5_c
63/63
Sources
Projects
Constellation www.aerospaceresearch.net/constellation
Distributed Ground Station Network www.hgg.aero Point of Contact Andreas HORNIG [email protected]
Software
AGI Satellite Tool Kit (STK) www.agi.com
I-DEAS www.plm.automation.siemens.com/de_de
ESATAN-TMS www.esatan-tms.com
TICRA Grasp & Champ www.ticra.com
10.02.12 Small Satellite Project 63