2. Raumfahrttechnologietage 2003

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1 2. Raumfahrttechnologietage 2003 Raumfahrtthemen am Institut für Strukturmechanik des DLR in Braunschweig Institutsbezeichnung: DLR, für Strukturmechanik

2 Solar Sail Technologies 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 km/h can be achieved by steady acceleration. For missions that make sense we need large structures with a mass-per-area relation of g/m². 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.

For missions that make sense we need large structures with a mass-per-area relation of 10-20 g/m².

3 Solar Sail Sail Craft Sail Unit for sequential Boom and Sail Deployment Service Unit for Telecommand, Telemetry and Data Management Orbital Platform as launcher interface and for power supply Kick Stage for Apogee kick impulse

and Data Management Orbital Platform as launcher

4 6. Solar Sail - Design and Verification ployable Solar Sail CFRP Boom: flexible lightweight design (100 g/m), scalability co-coiling of a specific number of booms (here: 4) CFRP material characterisation and selection thermal design, coating; test and analysis modular manufacturing; availability and scalability successful application of smart materials (R&D); improvement of damping rates; boom shape control Solar Sail boom contour tip amplitude [db] -17 db smart boom SAR boom contour

test and analysis modular manufacturing; availability and scalability successful application of smart materials (R&D);

5 Solar Sail - Development Steps & Boom Length 20 x 20m, In-Orbit Demo m Booms SAR Earth observation, 28m design study x 20m ESA/DLR, m Booms Potential Missions: Small Body Rendezvous / Sample Return (NEOs, Comets, Main Belt Asteroids) Solar Polar Orbiter (90 to the Ecliptic) Fast Missions to the Heliopause (200 AU in < 25 years) Single Instrument Boom 5m - 28m < 20m Thermal Shields 60x 60m, Asteroid Rendezvous 42m Booms

(NEOs, Comets, Main Belt Asteroids) Solar Polar Orbiter (90 to the Ecliptic) Fast Missions to the Heliopause

6 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

comet itsself Lander-Instruments : Emphasis on chemical composition

7 Rosetta Structure analysis Finite-Elemente Modell MSC/PATRAN v9.0 ROSETTA Lander Eigenfrequencyanalysis 8. Dezember 2003 First global Eigenfrequency at Hz 7

8 Rosetta - Payloadcarrier

9 Rosetta - Frame

10 Rosetta Solarbox

11 Rosetta - New Target Churyumov-Gerasimenko Launch date : Arrival : August 2014

12 System conditioning Mars 96 Wide Angle Optoelectronic Stereo Scanner - WAOSS for Mars 96 Mission Full Environmental Qualification and Acceptance Testing Climatic Chamber: Product Assurance Thermal Cycling Tests Temperature during Transportation Test Linear Accelerator: Resonance, Sine and Random Vibration Linear Acceleration Space Simulation Chamber: Thermal Vacuum Balance Tests Thermal Vacuum Cycling Tests Optical Calibration under Space Environment

Temperature during Transportation Test Linear Accelerator: Resonance, Sine and Random Vibration Linear

13 GR 9,202 14,15 14,9 14,17 5,15 4,5 15,9 8,4 4,3 11,4 9,17 15, ,18 16,9 3,8 1 8,4 8,11 9, ,9 1 0,1 4 2,10 5,6 2 01,106 10, , , ,1 00 9,10 9,19 9,104 GR 105, 100 Gr104, , System conditioning Cassini CDA Cosmic Dust Analyzer for the Cassini / Huygens Mission to Saturn Design and Construction Mechanical Engineering and Manufacturing Ther mal model and co mpo nents o f the CD A 16 cyli ndric part 1 out er 6 cyl indric part 1 inner 15 cyli ndric part 2 out er 5 cyl indric part 2 inner 14 cal ot te out er 4 calott e inner 2 mult ipl ie r 202high gai n 17 cover c alott e oute r 18 cover c alott e inner 11 chemic al t arget 3 che mical grid 8 targe t 10 main el ect roni cs 10 4 articu lati on mechani sm, mov articu lati on mechani sm, fix 10 6 CDA- suppo rt ri ng 20 1 S/ C- USSA 10 2 S/ C- BODY 4, 14 in ner sur faces g old 100 space 12 pyro 20 HRD-sen s 21 HRD- sen s 19 HRD asse mb 9 MLI- C DA Thermal Modeling Contamination problems Resonance, Sine and Random Vibration,Shock Testing Thermal Model blac k paint radi ati on c ond uct io n Complete Environmental Qualification Process and Flight Acceptance Tests Quality Assurance Concept Thermal Vacuum, Balance Testing Solar Vacuum Testing

nents o f the CD A 16 cyli ndric part 1 out er 6 cyl indric part 1 inner 15 cyli ndric part 2 out er 5 cyl indric part 2 inner 14 cal ot te out er 4 calott e inner 2 mult ipl ie r 202high gai n 17

14 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

Problems Experimental Analysis and Modalanalysis Full Environmental

15 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

Complete Environmental Qualification Process and Proto-Flight/Acceptance Tests Quality Assurance

16 System conditioning others & non-space applications Environmental Testing for different external Companies and Institutes AEG 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 Nextel Irradiation Test Surge Arrester Hi Gain Antenna Mechanism HTS

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

17 NetLander - CNES / DLR Project of 4 stations on Mars

18 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...)

19 Bepi Colombo future option ESA s cornerstone mission bound for Mercury ( 2 Orbiter + 1 Lander ) Landing scenario : before sunrise

20 Bepi Colombo lander structure Mercury Surface Element based on NetLander concept

Precision on earth. Reliability in space. RUAG Space.

Precision on earth. Reliability in space. RUAG Space. Image: ESA Precision on earth. Reliability in space. RUAG Space is the leading supplier of products for the space industry in Europe. Experience, outstanding