Abstract
The evaluation of Cramer-Rao bounds for elliptical orbits parameters estimates is presented. A special case of the observer moving near the orbit plane is considered. The observer motion being substituted by an equivalent motion on orbit plane results in a formulation of a simple two-dimensional model of motion-measurement, in which observing elevation angles are linked to the true anomalies and the orbit parameters via nonlinear equations. Differentiation of the equations by orbit parameters yields Jacobi's matrices of single angle measurements and finally the Fisher's information matrix that becomes a framework for accuracy analysis. The most sophisticated part of the Fisher's matrix evaluation - the reckoning of true anomalies derivatives by orbit parameters - is based on the numerical solution of the differential equation of motion by the Euler's method. Precision bounds of estimates for a certain family of orbits are evaluated in a wide range of practical burnout velocities and angles, so as apogee heights. The results obtained reveal high achievable accuracy for re-entry (landing) coordinates and apogee velocity components estimates utilizing elevation angle measurements only.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
