Satellite Micro-thruster with Thrust Control
Ing. Patricio Pedreira
Lic. Ricardo Lauretta
Dr. Sebastián D’hers
PRESENTATION TOPICS
• Problem Description
• CFD Model
• Validation & Results
• Conclusion and next steps.
Micro Thrusters problems
• Micro nozzle machining
– Electro-erosion
– Electro-chemical etching
– Specialized lathe machining
• Other solutions?
Planar Nozzles
Planar Nozzles
• Possible Limitations
– Increased boundary layer growth
– Higher shear stresses
– Minimun throat size
• Experimental & Computational Analisys
CFD model
• ANSYS 14.5
– Meshing: ICEM CFD
– Pre-Solver/Solver: CFX
– Postprocessing: CFD-Post
2D Model 3D Model
1.6 10^5 Elements 4.3 10^6 Elements
1.0 10^5 Nodes 4.2 10^6 Nodes
y+<1 y+<1
High-speed compressible flow SST k-ω Turbulence Model
High-speed compressible flow SST k-ω Turbulence Model
CFD model
• 2D & 3D Mesh
2D Model Results
Boundary layer effects are negligible for the prediction of thrust and
mass flow. This means that planar nozzles show no performance
disadvantages compared to axis-symmetrical ones.
Hypersonic nozzles have an advantage over supersonic nozzles
where Mach numbers are lower, as boundary layer effects on exit
Mach number does not affect nozzle performance.
2D Model Results
Nozzle boundary layer
development 100%
40%
3D Model Results
2.0 mm
1.0 mm
0.5 mm
Conclusion and next steps
• Nozzle length optimization
• High pressure simulations
• Prototype fabrication
• Control system design and fabrication
Acknowledgments
The authors would like to thank the support of
– Satellogic S.A.
– ITBACyT Funding
– Ing. Agustín Beceyro
– Luis De Cunto, José Zapata Usandivaras