Mayo, Alton Parker2022-06-292022-06-291961http://hdl.handle.net/10919/110993The present study was undertaken to determine the effects of the aerodynamics on a close earth orbit and reentry trajectory. The aerodynamic influence is compared to the effects of the earth’s oblateness, the sun, and the moon. In order to obtain maximum accuracy and computational speed Encke’s perturbative procedures were used during orbital periods and Cowell’s integration procedures during thrust and reentry periods.64 pages, 2 unnumbered leavesapplication/pdfenIn CopyrightLD5655.V855 1961.M39Drag (Aerodynamics)Perturbation (Mathematics)Space vehicles -- Atmospheric entryThesis