On the use of simplified calculation schemes for estimating the parameters of motion of space objects.
The paper formulates conditions, in the framework of the Newton method, under which spacecraft orbital parameters can be estimated by means of calculation of partial derivatives. The maximum likelihood method is applied to the estimation of the parameters of a satellite orbiting the equatorial plane of a spheroid, taking into account secular perturbations.
- Pub Date:
- November 1975
- Newton-Raphson Method;
- Orbit Calculation;
- Satellite Orbits;
- Iterative Solution;
- Maximum Likelihood Estimates;
- Orbit Perturbation;
- Partial Differential Equations;
- Secular Variations;