Orbit determination for powered flight space vehicles on deep space missions.

In this paper a study is made of the state estimation accuracies associated with the tracking of a powered flight space vehicle by the Deep Space Network facilities. The study utilizes a continuous data filter where random accelerations acting on the spacecraft are modeled as noise perturbing the differential equations of motion. The time histories of the state estimate uncertainties are illustrated over several passes of data, and the sensitivities of the uncertainties to the level of random acceleration, velocity, and position of the probe are noted. An application of the results to the navigation problem for a solar-electric Jupiter mission is presented, and the results of the application indicate that Earth-based, counted Doppler tracking is adequate for orbit determination for such a mission.