dtu space carbon fiber reinforced plastic and cfrp projects · dtu space carbon fiber reinforced...
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![Page 1: DTU Space Carbon Fiber Reinforced Plastic and CFRP projects · DTU Space Carbon Fiber Reinforced Plastic and CFRP projects Niels Christian Jessen Hans Ulrik Nørgaard-Nielsen](https://reader033.vdocument.in/reader033/viewer/2022051601/5ad573de7f8b9a5c638d1d93/html5/thumbnails/1.jpg)
DTU SpaceCarbon Fiber Reinforced Plastic and CFRP projects
Niels Christian Jessen Hans Ulrik Nørgaard-Nielsen
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January 31 2013NCJE HUNN
2 DTU Space, Technical University of Denmark
Why CFRP
+ Material properties can be designed
+ High Specific Stiffness Young's module / Density
+ High Thermal StabilityThermal Conductivity / Coefficient of Thermal expansion
+ High StrengthUltimate strength / Density
- Moisture sensitive
- Radiation
- Outgassing
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January 31 2013NCJE HUNN
3 DTU Space, Technical University of Denmark
CFRP Manufacturing methods
Filament Winding
Prepreg
Woven mesh
Prepreg
Injector molding
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4 DTU Space, Technical University of Denmark
Micro Mechanics
Variables ofLaminaUD UniDirectionalLayer
• Fiber type• Matrix• Fiber Volume
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5 DTU Space, Technical University of Denmark
Macro Mechanics
• Fiber lay upo Angleso Number of layerso Combination of
Lamina layers
• Laminate program
• FEM
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January 31 2013NCJE HUNN
6 DTU Space, Technical University of Denmark
Symmetric Lay Up
• Symmetric around center of Laminate avoids out of plane effects for plates.
• Tubes are special case
Post Curing shapes of
Unsymmetrical Laminates
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January 31 2013NCJE HUNN
7 DTU Space, Technical University of Denmark
Behavior of lay up in Laminate
Bending: stiff
Torsion: soft
Bending: soft
Torsion: Stiff
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January 31 2013NCJE HUNN
8 DTU Space, Technical University of Denmark
Quasi isostropic Lay up
• In Plane:o Equal mechanical
properties in all directions.
• Out of Plane:o Different properties
since dominates by matrix material
Layers
1 -60⁰
2 0⁰
3 60⁰
Remember symmetry for plates
Layers
1 45⁰
2 0⁰
3 -45⁰
4 90⁰
Remember symmetry for plates
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January 31 2013NCJE HUNN
9 DTU Space, Technical University of Denmark
Space environments• Ultra high Vacuum
• Cooling only by radiation• Cavities must be avoided• Outgassing
• Extreme temperature• Cryo to very high temperatures• Dimensional Stability
• Radiation
• Static electricity
• Reliable• No possibilities for repair and adjustments
• Extreme launch loads• High g-loads (20 g and more not unusual in vibrations)
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January 31 2013NCJE HUNN
10 DTU Space, Technical University of Denmark
Planck
•Mapping the Cosmic Microwave Background anisotropies with improved sensitivity and angular resolution
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Planck Satellite
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January 31 2013NCJE HUNN
12 DTU Space, Technical University of Denmark
Planck Satellite Reflectors
ESA Project:
DTU Space:Principal Investigator for the Reflector system.
74 detectors.
9 frequencies.
30 – 857 GHz.
Launch: May 14 2009.
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13 DTU Space, Technical University of Denmark
PlanckCFRP-Reflectors
Qualification Model Secondary Reflector in 3D measurement machine.Dimensions 1051mm x 1104mm.Weight 13.6 Kg.
Flight Model Primary Reflector Shown in aluminizing plant.Dimensions 1556mm x 1887mm.Weight 29.2 Kg.
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14 DTU Space, Technical University of Denmark
Design af reflektorer til Planck
Skin.
Honeycomb.
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PlanckDimpling, Sandwich
666932 Nodes.486024 Elements.
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PlanckInfluence from adhesive. Main expected Dimpling due to cool-down from Room Temperature to 41 K.
L20/SL, Aerosil Quarts Powder.Dimpling 2.4 µm.Original adhesive.
2216 Gray.Dimpling 0.4 µm.New adhesive.
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17 DTU Space, Technical University of Denmark
PlanckLift Of
Lift OfMay 14 2009Kl. 10:12:07KourouFrench Guiana
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James Web Space TelescopeMIRI
6.5 m Space telescope.
NASA/ESA Project.
L2.
3 Instruments.
Launch 2017.
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19 DTU Space, Technical University of Denmark
MIRI/JWSTInfrared spectrograph
MIRI
A combined mid infrared camera and spectrograph covering wavelengths 5-27 µm.
DTU Space:Responsible of the Primary Support Structure.
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MIRI/JWSTPrimary Support Structure
Design drivers:
Low thermal conductivity between the 7K cold instrument and the 35 K ’hot’ telescope.
Lowest Eigenfrequency above 60 Hz with a 103 Kg instrument.
Max g-load 20.
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MIRI/JWSTPrimary Support Structure Tests:
Thermal cycling from Room Temperature to 7 K.
Strength Test.
Vibration.
Material properties:
Young's module.
Coefficient of thermal expansion.
Coefficient of moisture expansion.
Thermal conductivity.
Out gassing.