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