Raumfahrtthemen am Institut für Strukturmechanik … · Raumfahrtthemen am Institut für Strukturmechanik des DLR in Braunschweig [email protected]. 2 8. Dezember 2003 DLR,

Institutsbezeichnung:Que

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DLR, Institut für Strukturmechanik

2. Raumfahrttechnologietage 2003

Raumfahrtthemen am Institut für Strukturmechanik

des DLR in Braunschweig

[email protected]

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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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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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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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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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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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Finite-Elemente Modell MSC/PATRAN v9.0

ROSETTA Lander Eigenfrequencyanalysis

First global Eigenfrequency at 82.55 Hz

Rosetta – Structure analysis

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Rosetta - Payloadcarrier

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Rosetta - Frame

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Rosetta – Solarbox

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Rosetta - New Target Churyumov-Gerasimenko

Launch date : 29-02-2004

Arrival : August 2014

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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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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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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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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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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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NetLander - CNES / DLR Project of 4 stations on Mars

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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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Bepi Colombo – future option

ESA´s cornerstone mission bound for Mercury ( 2 Orbiter + 1 Lander )

Landing scenario : before sunrise

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Bepi Colombo – lander structure

Mercury Surface Element based on NetLander concept

Documents

Raumfahrtthemen am Institut für Strukturmechanik … · Raumfahrtthemen am Institut für Strukturmechanik des DLR in Braunschweig [email protected]. 2 8. Dezember 2003 DLR,