Abstract
The problem of short arc orbit determination with the data from a single station during the early orbital phase of a launch vehicle mission poses challenges. In this paper after a review of various methods an efficient U-D covariance factorization filtering algorithm is adopted for early orbit determination with limited data. It exhibits improved numerical characteristics particularly in ill conditioned problems. The early orbit determination algorithm considers data over a duration of 150 sec from a single tracking station at one sample per sec and computes the orbit sequentially. As an illustration a nominal 400 km circular orbit is considered. Keplerian model is used. Range, azimuth and elevation data combination results in best orbit estimate. The reduction in position error is very rapid. However, the velocity error reduces gradually. The algorithm converges for very large uncertainty in initial state.
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© 1986 D. Reidel Publishing Company
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Raju, D.S.R., Rao, C.S., Shrivastava, S.K. (1986). Early Orbit Determination Using U-D Covariance Propagation Filter. In: Bhatnagar, K.B. (eds) Space Dynamics and Celestial Mechanics. Astrophysics and Space Science Library, vol 127. Springer, Dordrecht. https://doi.org/10.1007/978-94-009-4732-0_29
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DOI: https://doi.org/10.1007/978-94-009-4732-0_29
Publisher Name: Springer, Dordrecht
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