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Covariance Estimation and Autocorrelation of NORAD Two-Line Element Sets60,99 €![Effects of Air Drag and Lunar Third-Body Perturbations on Orbital Motion Near a Reference Kam Torus]( "Effects of Air Drag and Lunar Third-Body Perturbations on Orbital Motion Near a Reference Kam Torus")
Effects of Air Drag and Lunar Third-Body Perturbations on Orbital Motion Near a Reference Kam Torus60,99 €![Instrumentation for Continuously Recording Plasma-Induced Frequency Shifts of Two Microwave Cavity Resonances]( "Instrumentation for Continuously Recording Plasma-Induced Frequency Shifts of Two Microwave Cavity Resonances")
Instrumentation for Continuously Recording Plasma-Induced Frequency Shifts of Two Microwave Cavity Resonances60,99 €![Modeling GPS Satellite Orbits Using KAM Tori]( "Modeling GPS Satellite Orbits Using KAM Tori")
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Investigating the Use of Frequency Selective Surfaces in High Power Microwave Applications60,99 €![Process for Refining and Validating a Finite Element Model of an Experimental High-Altitude, Long-Endurance (Hale) Aircraft]( "Process for Refining and Validating a Finite Element Model of an Experimental High-Altitude, Long-Endurance (Hale) Aircraft")
Process for Refining and Validating a Finite Element Model of an Experimental High-Altitude, Long-Endurance (Hale) Aircraft60,99 €
The Kolmogorov Arnold and Moser (KAM) theorem states that a lightly perturbed Hamiltonian system will have solutions which lie on a torus. The trajectories of Earth orbiting satellites have been shown to lie on KAM tori with three basis frequencies. These basis frequencies are determined by fitting second order polynomials to data from Two-Line Element sets (TLEs) using a least squares technique. The first order coefficients are used as the torus basis frequencies while the second order coefficients are used to account for perturbations to the satellite's orbit such as air drag. Four cases are attempted using the Hubble Space Telescope and three rocket bodies as test subjects. A KAM torus with the desired basis frequencies is constructed and used to predict satellite position. This position prediction is compared to the position obtained from TLEs using Simplified General Perturbations 4 (SGP4) algorithms. Analysis of the torus position error shows that the torus construction algorithm does not fully characterize the contribution of the smaller basis frequencies to the orbital trajectory.