Multiple Satellite Trajectory Optimization

Abstract

This thesis develops and validates a satellite trajectory optimization model. A summary is given of the general mathematical principles of dynamic optimal control to minimize fuel consumed or transfer time. The dynamic equations of motion for a satellite are based upon equinoctial orbital elements in order to avoid singularities for circular or equatorial orbits. The study is restricted to the two-body problem, with engine thrust as the only possible perturbation. The optimal control problems are solved using the general purpose dynamic optimization software, DIDO. The dynamical model together with the fuel optimal control problem is validated by simulating several well known orbit transfers. By replicating the single satellite model, this thesis shows that a multi-satellite model which optimizes all vehicles concurrently can be easily built. The specific scenario under study involves the injection of multiple satellites from a common launch vehicle; however, the methods and model are applicable to spacecraft formation problems as well.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 2004
Accession Number
ADA429834

Entities

People

  • Paul B. Mendy Jr

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Artificial Satellites
  • Computer Programming
  • Computer Programs
  • Computers
  • Differential Equations
  • Elliptical Orbits
  • Equations
  • Equations Of Motion
  • Equatorial Orbits
  • Launch Vehicles
  • Mathematics
  • Operating Systems
  • Orbital Elements
  • Orbits
  • Spacecraft
  • Trajectories

Readers

  • Operations Research
  • Robotics and Automation.
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Space
  • Space - Orbital Debris
  • Space - Spacecraft Maneuvers