Orbit determination error analysis and a station-keeping strategy for sun-earth L1 libration point orbits

Details Orbit determination error analysis and a station-keeping strategy for sun-earth L1 libration point orbits Orbit determination error analysis and a station-keeping strategy for sun-earth L1 libration point orbits

Apr 1994

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994jansc..42..207h&link_type=abstract

Journal of the Astronautical Sciences (ISSN 0021-9142), vol. 42, no. 2, p. 207-228

Astronomy and Astrophysics

Astronomy

1

Earth (Planet), Error Analysis, Libration, Orbit Calculation, Space Platforms, Spacecraft Orbits, Stationkeeping, Sun, Trajectory Control, Computerized Simulation, Environment Effects, Errors, Interplanetary Trajectories, Spacecraft Trajectories, State Vectors

Scientific paper

Spacecraft in orbits near the interior libration point in the Sun-Earth system are excellent platforms for scientific investigations concerning solar effects on the terrestrial environment. Since such libration point trajectories are generally unstable, spacecraft moving on these paths must use some form of trajectory control to remain close to their nominal orbit. An integral part of any station-keeping investigation is estimation of the spacecraft state vector. The trajectory estimation process will be affected by many sources of error. Several orbit determination error analysis methods are mentioned and some results are summarized. The primary goal of this effort, however, is the development of a station-keeping strategy applicable to such trajectories. This approach uses maneuvers executed (impulsively) at discrete time intervals. The analysis includes some investigation of a number of the problem parameters that affect the overall maneuver costs. Simulations are designed to provide representative station-keeping costs for a spacecraft moving in a libration point trajectory; preliminary results are summarized.

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