We research propulsion solutions that enable new classes of space missions, working at the intersection of propulsion hardware and mission design. We research high efficiency electric propulsion systems for spacecraft to improve upon their designs and feasibility of mission integration. Our long term goals are to enable sustainable exploration of the solar system starting with propellant depots in Earth and lunar orbits and extending to interplanetary architectures. 

Research Areas:

Designing Propulsion systems for In-Situ Resource Compatability

We have been studying the efficacy of replacing traditional noble gas propellants used in plasma propulsion devices with gaseous water. We have analyzed plasma generation efficiency which is applicable to a range of propulsion devices [1] and the efficiency of various non-contact plasma acceleration schemes [2,3]. Methods we have used include plasma-chemical analyses coupled with particle-in-cell modeling and quasi-1D plasma flow approximations. Our current research focus involves the study of dual-mode devices for flexible mission architectures using a shared propellant and efficiency improvements for water-plasma devices.

[1] Petro and Sedwick, Effects of Water Vapor Propellant on Electrodeless Thruster Performance, AIAA Journal of Propulsion and Power, 2017.

[2] Petro, Brieda, and Sedwick, PIC Simulations of Chemistry Effects in an Electrodeless Water Plasma Thruster, Proceedings of AIAA Propulsion and Energy Forum, 2019.

[3] Petro and Sedwick, Effects of Water Vapor Propellant on Helicon Thruster Performance, Proceedings of AIAA Propulsion and Energy Forum, 2016.

Kinetic Ion Beam Modeling for Electrospray Thrusters

Sustainable space exploration requires longevity and flexibility in satellite platforms. For small satellites, compact electric propulsion devices such as electrospray thrusters can significantly extend lifetime and capability. As these devices operate under different principles and with more complex propellants than traditional plasma thrusters, fundamental modeling of the ion emission process and plume-spacecraft interactions are required. Towards this end, we have developed a kinetic model of the plume evolution of an electrospray ion source that tracks processes at the individual ion level. This model can be used to predict the trajectory of plume ions and neutral bi-products and their impact on performance. As a spacecraft-integrated device would have thousands of emission sites, further research will include the physics of the composite plume.

[1] Petro, Miller, Schmidt, and Lozano, Development of a Fragmentation Model for Kinetic Plume Modeling, Proceedings of the International Electric Propulsion Conference, 2019.


Electric Propulsion and Mission Design 

The choice of propulsion system is deeply tied to mission objectives and spacecraft properties. Electric propulsion systems often enable missions that are otherwise infeasible with less fuel-efficient propulsion architectures. For these missions, the propulsion system, spacecraft, and trajectory are closely coupled throughout the formulation and design process. We are interested in exploring new ways that electric propulsion and other revolutionary architectures can enable new solar system science and we are working to develop tools to explore this design space more efficiently.


[1] Petro and Sedwick, Survey of Moderate-Power Electric Propulsion Systems, Journal of Spacecraft and Rockets, Vol. 54, No. 3, 2017.

[2] Sheerin, Petro, Lozano, and Lubin, Fast Solar System Transportation with Electric Propulsion Powered by Directed Energy, Acta Astronautica, vol. 179, 2021.

[3] MacKensie, et. al., THEO Concept Mission: Testing the Habitability of Enceladus’s Ocean, Advances in Space Research, Vol. 58, No. 6, 2016.