Impact of launch injection errors on orbit-raising of all-electric satellites
MetadataShow full item record
To mitigate the cost of chemical propulsion satellites, satellite operators are increasing their utilization of all-electric propulsion satellites for orbit-raising missions to geosynchronous equatorial orbit. However, the use of electric propulsion increases the transfer time of a mission. An increase in transfer time makes the uncertainties in the initial states of the satellite have a larger effect on the mission. These uncertainties could require delayed satellite operations or reduced mission lifetimes causing lost revenue for the operators. The purpose of this thesis is to investigate the effect of uncertainty on the orbit-raising missions of all-electric satellites to geosynchronous equatorial orbit. The uncertainty that is considered represents the injection error of the satellite’s initial states, and it is characterized by the mean and covariance matrix of the initial satellite states. In this thesis, a method for propagating the uncertainties in the satellite states of the injection orbit during an electric orbit-raising mission is developed using Monte Carlo simulations. Additionally, the computational cost and benefits of using an unscented transformation method instead of a Monte Carlo method to reduce computation time are investigated by comparing the results after numerical simulations. Scenarios involving typical launch injection errors as well as large injection errors due to anomalies are considered to understand their effect on final transfer time and final mass. Ultimately, these frameworks can be used by mission designers and satellite operators to assess the effects of launch uncertainties on their missions.
Thesis (M.S.)-- Wichita State University, College of Engineering, Dept. of Aerospace Engineering