Atmospheric density corrections for satellite orbit determination and prediction in an operational environment.

摘要

The current popular climatological atmospheric models do not produce an accurate density estimate in the short term. The result for the operational satellite orbit determination system is an incorrect ballistic coefficient and poor three-day ephemeris predictions. Three-day ephemeris predictions are used routinely for collision avoidance screening on high drag satellites, making accurate predictions a necessity for the safety of manned space flight.; Several methods for improving the density estimation have been developed but none have proven operationally implementable. A method to produce a corrected atmospheric density estimation is outlined for use in this unique environment. This work was performed using a prototype of the operational orbit determination system and developed with operational use in mind.; To improve the density estimation of the operational atmospheric model, density multipliers are derived for five separate high drag satellites. These density multipliers are shown to improve the estimate of orbit determination and prediction for collision avoidance. A fitting method to obtain daily density multipliers from the ones derived from the five calibration satellites is also outlined. In addition, a method to predict the density multipliers for three days is developed.