1. Laser Astronaut Retrieval Propellant Development
Tyler Baxter1, John E. Sinko1,2, Clifford Schlecht2, and Mark Gill3
¹ Dept. of Physics and Astronomy, Saint Cloud State University, St. Cloud, MN 56301
² Institute for Materials, Energetics and Complexity, St. Cloud, MN 56301
³ ISELF 3D Printing Coordinator, Saint Cloud State University, St. Cloud, MN 56301
MOTIVATION
The development of the aerospace industry has recognized
the need for a method of retrieving both assets and humans
in the vacuum environment. This experimental process
explores and refines the idea of using lasers to create a
‘tractor beam’ retrieval effect by controlled laser ablation
using low-cost, low-risk propellant alternatives.
EXPERIMENTAL PROCEDURE
To demonstrate quantitative propellant thrust, an improvised 3D-
printed ablatant chamber casing was housed directly atop a force
sensor capable of measuring a thrust response. All components
were sealed under a vacuum chamber in which we plan to simulate
low-Earth orbit vacuum conditions.
Acknowledgements
This project was funded by the authors and by Saint Cloud
State University. The authors would also like to express thanks
to Dr. Michael Dvorak and Dr. Michael Jeannot of the Saint
Cloud State Chemistry Department for their input.
1. Target Irradiation
Targets were exposed to 30-
seconds of 3 watts continuous
laser output at a wavelength
of 514.5 nm.
2. Target Ablation
Following direct exposure,
ablatant targets offgas
residual chemical products
that fill the volume of the
ablation chamber.
3. Coordinated
Confinement
Residual byproducts of the
ablation process are directed
out of the casing through a
1mm diameter steel tubule to
be redirected for use
elsewhere as needed.
Figure 1. Ablation casing diagram.
References
1. National Aeronautics and Space Administration, NASA Strategic
Plan 2014, pp. 3, 11.
2. S. Yokoyama, H. Horisawa, I. Funaki, and H. Kuninaka,
“Fundamental Study of Laser Micro Propulsion Using Powdered-
Propellant” in International Electric Propulsion Conference, IEPC-
2007-230, pp. 1-7 (2007).
3. C. R. Phipps, J. R. Luke, G. G. McDuff, T. Lippert, “Laser-driven
micro-rocket”, Appl. Phys. A 77, pp. 193-201 (2003).
4. M. S. Egorov, Yu. A. Rezunkov, E. V. Repina, and A. L. Safronov,
“Laser corrective propulsion plant for spacecraft”, J. Opt. Technol.
77(3), pp. 159-164 (March 2010).
5. 9. J. T. Kare, “Laser Powered Heat Exchanger Rocket for Ground-to-
Orbit Launch”, J. Propulsion and Power, 11(3), pp. 535-543 (1995).
Figure 2. Ablation of propellant.
Figure 3. Dispersion of byproducts into
casing microtubule.
RESULTS
Using a carbon nanofoam propellant:
Figure 4. Experimental ‘tractor beam’ thrust response for carbon sample.
Figure 5. Magnification (80x) of carbon
foam propellant sample.
Figure 6. Carbon foam propellant casing.
Using a thin film ammonium carbonate propellant:
Figure 7. Size representation of the ammonium carbonate ablation casing.
Figure 8. Magnification (2.5x) of ammonium
carbonate crystals.
Figure 9. Live ablation of ammonium
carbonate target in vacuum.
ANALYSIS AND FUTURE WORK
Although the experiment was successful, several
further methods of refinement are possible. Future
work will include design of an ablation casing with a re-
sealable gasket to allow for swift comparison of other
carbonate-related compounds and minimal loss of
desired offgassed products.
Figure 10. Carbon ablation target irradiated by 514.5nm photons.