Dynamic Mission Modeling and Simulation: Application of Micro-Vacuum Arc Thrusters and Frozen Orbits
Open AccessThe dynamic mission modeling and simulation of scenarios around the Earth, Moon, and libration points are used to explore the application of the Vacuum Arc Thruster and frozen orbits for future space exploration missions. The Micro-Vacuum Arc Thruster (µVAT) is a propulsion system that uses an arc to evaporate solid cathode material. The propulsion system is compatible for nano-satellite applications due to its low operating voltage, low mass, and its simplicity to be integrated into the spacecraft operating system. The µVAT experimental performance values were used to baseline the numerical thruster model for the space mission operational scenarios. The simulation results were used analyze and make recommendations on the performance parameters that are required for manuevers and interplanetary trajectories for space exploration missions. In addition, the analytical derivation and numerical analysis of Earth-based frozen orbits are used to baseline the low-altitude, frozen orbits. A high resolution in order and degree lunar gravity model and third-body perturbations due to the Earth and Sun are included in the detailed simulation. The time evolution of the classical frozen orbital conditions is calculated by numerically propagating the orbits in an environment where all the perturbations are included. The behaviour and evolution pattern of the orbital elements are used to baseline a set of numerical quasi-frozen conditions for a series of low-altitude, polar orbits. The numerically integrated results for a family of polar frozen orbits provide insight into the predictive behaviour pattern and evolution of the orbital elements that can be extended to any given set of initial conditions and requirements. It is shown that these results are not a fixed point solution that is calculated for a selective set of perturbations, but rather the numerical model can be used to determine a set of conditions and orbital elements to satisfy a given set of mission operational requirements for a low-maintenance orbit. The results from the mission modeling and simulation provided insight to a selection of frozen orbits along with the VAT propulsion subsystem that can be used as a low-cost, high performance solution for future CubeSat science and exploration missions that are looking to go beyond the boundaries of the Earth.
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