Institutsbezeichnung:Que
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DLR, Institut für Strukturmechanik
2. Raumfahrttechnologietage 2003
Raumfahrtthemen am Institut für Strukturmechanik
des DLR in Braunschweig
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DLR, Institut für Strukturmechanik
Solar Sail – Technologies
Deployment Technology The key elements are 4 carbon fiber composite booms that consist of 2 adhesively connected half shells.In the stowed configuration the booms are flat and can be spooled.
Propulsion Technology Solar sails utilize the „light pressure“ of the sun (i.e. photons) that hit on a large reflecting area. On a low „thrust“ level velocities up to 360 000 km/h can beachieved by steady acceleration. For missions that make sense we need large structures with a mass-per-area relation of 10 - 20 g/m².
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DLR, Institut für Strukturmechanik
Solar Sail – Sail Craft
Sail Unitfor sequential Boom and Sail Deployment
Orbital Platformas launcher interface and for power supply
Service Unitfor Telecommand, Telemetry and Data Management
Kick Stagefor Apogee kick impulse
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DLR, Institut für Strukturmechanik
Solar Sail - Design and Verification
Solar Sail boom contour
SAR boom contour
6.
Deployable Solar Sail CFRP Boom:
n flexible lightweight design (100 g/m), scalability
n co-coiling of a specific number of booms (here: 4)
n CFRP material characterisation and selection
n thermal design, coating; test and analysis
n modular manufacturing; availability and scalability
n successful application of smart materials (R&D); improvement of damping rates; boom shape control
frequency [Hz]
tip
am
plit
ud
e [d
B]
smart boom
-17 dB
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DLR, Institut für Strukturmechanik
SAR Earth observation, 28m design study
Solar Sail - Development Steps & Boom Length
20 x 20m ESA/DLR, 199914m Booms
20 x 20m, In-Orbit Demo 200514m Booms
Potential Missions:
Small Body Rendezvous / Sample Return (NEOs, Comets, Main Belt Asteroids)Solar Polar Orbiter (90° to theEcliptic)Fast Missions to the Heliopause(200 AU in < 25 years)
60x 60m, Asteroid Rendezvous42m Booms
Single Instrument Boom
5m - 28m
< 20m Thermal Shields
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DLR, Institut für Strukturmechanik
Rosetta – Scientific tasks
Orbiter-Instruments :Emphasis on comet coma, magnetic effects with the solar wind, investigation of the comet itsself
Lander-Instruments :Emphasis on chemical composition of the comet (organic substances!), local structure of the comet surface
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DLR, Institut für Strukturmechanik
Finite-Elemente Modell MSC/PATRAN v9.0
ROSETTA Lander Eigenfrequencyanalysis
First global Eigenfrequency at 82.55 Hz
Rosetta – Structure analysis
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DLR, Institut für Strukturmechanik
Rosetta - New Target Churyumov-Gerasimenko
Launch date : 29-02-2004
Arrival : August 2014
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DLR, Institut für Strukturmechanik
System conditioning – Mars 96
Wide Angle Optoelectronic Stereo Scanner - WAOSS for Mars 96 Mission
Full Environmental Qualification and Acceptance Testing
Climatic Chamber:Product AssuranceThermal Cycling TestsTemperature during Transportation Test
Linear Accelerator:Resonance, Sine and Random VibrationLinear Acceleration
Space Simulation Chamber: Thermal Vacuum Balance TestsThermal Vacuum Cycling TestsOptical Calibration under Space Environment
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DLR, Institut für Strukturmechanik
System conditioning – Cassini CDA
Cosmic Dust Analyzer – for the Cassini / Huygens Mission to Saturn
Design and Construction
Mechanical Engineering and
Manufacturing
Thermal Modeling
Contamination problems
Complete Environmental Qualification
Process and Flight Acceptance Tests
Quality Assurance Concept
Resonance, Sine and Random Vibration,Shock Testing
12 pyro20 HRD-sen sor K21 HRD-sen sor G
19 HRD asse mbly 9 MLI- CDA
100 space
radi ati onc onduct ion
3,8
2 ,10
4, 3
11, 4
4,14
15 ,1 6
16, 9
5, 15
15 ,9
1 7, 18
1 8, 4
14, 17
1 0,1 4
2 01, 106
9, 10
9,19
10 2, 100
10 2,1 00
5 ,6
9 ,17
14 ,9
8, 11
9,1 00
16, 9
8, 4
4, 5
14, 15
Ther mal model and components o f the CDA
16 cylindric part 1 outer 6 cyl indric part 1 inner15 cylindric part 2 outer 5 cyl indric part 2 inner14 calot te outer 4 calotte inner 2 mult ipl ie r202high gain
17 cover c alotte oute r 18 cover c alotte inner 11 chemic al t arget 3 che mical grid 8 targe t 10 main elect ronics 10 4 articu lati on mechani sm, mov.
10 5 articu lati on mechani sm, f ix 10 6 CDA- suppo rt ri ng 20 1 S/ C- USSA 10 2 S/ C- BODY
10, 104
104, 105
105 ,106
GR 9,202
9,104
GR 105, 100
Gr 104, 100
in ner sur facesg old
blac kpaint
Thermal Model
Thermal Vacuum, Balance TestingSolar Vacuum Testing
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DLR, Institut für Strukturmechanik
System conditioning - MOS
Modular Optoelectronic Scanner – MOS
Development of Finite Element Models (FEM)
Solving of FEM for Statical and Dynamical Problems
Experimental Analysis and Modalanalysis
Full Environmental Qualification and Acceptance Testing
FEM Model of MOS
MOS Spectrometer at Analysis
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DLR, Institut für Strukturmechanik
System conditioning - Bird
Bi-spectral Infra-Red Detection for BIRD
Design and Construction
Mechanical Engineering and Manufacturing
Thermal Modeling
Structure Modeling and Analysis
Complete Environmental Qualification Process and Proto-Flight/Acceptance Tests
Quality Assurance concerning Environmental Testing
Vibration tests on Shaker Tiravib
Integration into Space Simulation Chamber
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DLR, Institut für Strukturmechanik
System conditioning – others & non-space applications
Environmental Testing for different external Companies and InstitutesAEG
Aucoteam GmbH
Astrium Bremen/Friedrichshafen
Baumer Optronik GmBH Radeberg
Berliner Institut für Optik GmbH
Daimler-Benz Aerospace
Danish Space Research Institute
Deutsche Bahn AG
Dornier Satellitensysteme GmbH
Dräger Aerospace GmbH
Forschungszentrum Jülich
FPM Space Sensor GmbH
Geo-Forschungszentrum Potsdam (Champ)
HTS AG Switzerland
Jena Optronik GmbH
Kayser Threde GmbH
Max Planck Institut für Aeronomie
Raumfahrt und Systemtechnik GmbH RST Rostock
Siemens AG
STN Atlas Elektronik
Technical University of Denmark
Rosetta VIRTIS Main Electronic Box
Surge Arrester
Nextel Irradiation TestHi Gain Antenna Mechanism HTS
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DLR, Institut für Strukturmechanik
NetLander - CNES / DLR Project of 4 stations on Mars
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DLR, Institut für Strukturmechanik
NetLander - Current Status
2 breadboard models built
Successful drop tests and uprighting tests
Detailed FE-Model and numerical analysis
Political / financial problems
( CNES-ESA negotiations...)
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DLR, Institut für Strukturmechanik
Bepi Colombo – future option
ESA´s cornerstone mission bound for Mercury ( 2 Orbiter + 1 Lander )
Landing scenario : before sunrise