Accession Number : AD1028884


Title :   Military Applications of High-Altitude Satellite Orbits in a Multi-Body Dynamical Environment Using Numerical Methods and Dynamical Systems Theory


Descriptive Note : Technical Report,01 Aug 2014,24 Mar 2016


Corporate Author : AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH WRIGHT-PATTERSON AFB United States


Personal Author(s) : Wilmer,Meredith M


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/1028884.pdf


Report Date : 01 Mar 2016


Pagination or Media Count : 217


Abstract : The circular restricted three-body problem (CR3BP) is a simplified dynamical model for a satellite under the gravitational influence of both the Earth and the Moon, maintaining closer fidelity to the gravitational environment experienced by a high-altitude Earth-orbiting spacecraft than modeling in the Earth-satellite two-body problem. Resonant orbit arcs are used to determine an initial guess to input into an algorithm that computes a trajectory solution with specific design requirements and constraints. A test case uses this method to compute a lunar fly-by transfer solution requiring less than two-body transfer methods and offers an unusual pathway that adds an unpredictability element to the design. Multiple-shooting and pseudo-arc length continuation methods are used to target trajectories and compute periodic orbits in the CR3BP to within a satisfactory tolerance. Invariant manifolds from an unstable periodic orbit around a liberation point in the Earth-Moon system are used as unpredictable transfer pathways when traveling from one Earth orbit to another, utilizing a map-based design process. Periapsis Poincare maps are also constructed to characterize the observed behaviors of orbits in the Earth-Moon system for a specified time, demonstrating utility for both designing trajectories with desired end characteristics and predicting an unknown spacecraft's future behavior.


Descriptors :   apogees , spacecraft , celestial mechanics , geosynchronous orbits , transfer orbits , elliptical orbits , differential equations , spacecraft orbits , cartesian coordinates , earth orbits , low earth orbits , perigees , satellite orbits , Nonlinear analysis


Subject Categories : Unmanned Spacecraft
      Theoretical Mathematics
      Celestial Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE