Optimal Non-Coplanar Launch to Quick Rendezvous

Abstract

The purpose of this study was to determine the feasibility of launching a Delta Clipper-like vehicle on an optimal, non-coplanar trajectory to rendezvous with an earth orbiting object in one orbit or less. The focus of the research was to determine what such a trajectory would look like, and to determine the cost, in payload mass, of flying such a trajectory. A model for the ascent trajectory was developed using the dynamics equations of motion, an atmosphere model, and an aerodynamic model for the DC-Y concept vehicle. A boundary value problem was posed and solved for a coplanar rendezvous. The non-coplanar solutions were obtained through extrapolation from the coplanar solution.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1997
Accession Number
ADA335740

Entities

People

  • Gregory B. Sears

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Algorithms
  • Ascent Trajectories
  • Atmospheres
  • Boundaries
  • Boundary Value Problems
  • Differential Equations
  • Earth Orbits
  • Equations
  • Equations Of Motion
  • Equations Of State
  • Flight Paths
  • Low Earth Orbits
  • Rendezvous
  • Space Stations
  • Spacecraft
  • Trajectories

Readers

  • Control Systems Engineering.
  • Database Systems and Applications
  • Unmanned Aerial System (UAS) Autonomous Capabilities and Mission Reconnaissance.

Technology Areas

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