Determination of the orbit of a spacecraft and all the constant and dynamic parameters that affect the orbit is an application of estimation theory. A model of the spacecraft motion as a function of initial conditions and certain constant and dynamic parameters is developed that may be used to predict the flight path and compute the value of measurements that are obtained during the space flight. Orbit determination involves adjusting the value of the independent parameters that need to be determined until the computed measurements are close to the actual measurements. Since there are many more measurements than independent parameters, the solution is found that minimizes the error in the measurements. This solution will also minimize the error in the estimated parameters.
Orbit Determination
Space Technology Library
2025-06-06
40 pages
Article/Chapter (Book)
Electronic Resource
English
Process noise , Line of nodes , Data signature , Canberra , Madrid , Weighted least squares , Computed measurement , Deep Space Network (DSN) , Kalman, R. E. , Continuous , Direct orbit determination , Newton-Raphson , Data residual , Computed covariance , Line of sight , Hamilton , Melbourne , Discrete process noise , Goldstone , Shur’s identity , Anderson , Plane of sky , Process noise duality , Signature , Riccati , A priori , Discrete data update , Data equation , Data update , Kalman filter , Occultation , Shur , Consider covariance , Convergence , Smoothing Software Engineering/Programming and Operating Systems , Space Sciences (including Extraterrestrial Physics, Space Exploration and Astronautics) , Mathematical Applications in Computer Science , Physics and Astronomy , Aerospace Technology and Astronautics , Engineering
Wiley | 2024
|NTRS | 1993
|NTRS | 1965
|NTIS | 1965
|AIAA | 1996
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