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Copernicus, A Generalized Trajectory Design and Optimization System. Greg Johnson Sebastian Munoz The University of Texas at Austin November 25, 2003. Overview. What is trajectory design and optimization? What makes this problem so difficult?

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copernicus a generalized trajectory design and optimization system

Copernicus, A Generalized Trajectory Design and Optimization System

Greg Johnson

Sebastian Munoz

The University of Texas at Austin

November 25, 2003

overview
Overview
  • What is trajectory design and optimization?
  • What makes this problem so difficult?
  • The necessity for a generalized trajectory system
  • Existing systems
  • The Copernicus trajectory system
  • Conclusions
what is trajectory design and optimization

Trajectory produced with Copernicus, created in SOAP by Sebastian Munoz

What is trajectory design and optimization?
  • Finding the best trajectories for a given mission
  • Example: Moon Capture
    • Earth/Moon trajectory
    • Ballistic
      • 3rd body perturbation
what makes this problem so difficult
What makes this problem so difficult?
  • What is the best trajectory?
    • Minimized parameters
      • Total ΔV
      • Time of flight
    • Maximized parameters
      • Payload capacity
      • Excess fuel
  • Finding a trajectory with optimal values for one or all of these parameters
the necessity of a general system
The necessity of a general system
  • General
    • “Not limited in scope, area or application” –The American Heritage Dictionary of the English Language
  • Capabilities of a general system
    • ΔV minimization
    • Time of flight minimization
    • Payload maximization
    • Excess fuel maximization
    • Multiple segments for a trajectory
  • Such a system would satisfy the needs for any mission, including complex interplanetary trajectories
some other systems
Some other systems
  • VARITOP
  • CHEBYTOP
  • MIDAS
  • SEPSPOT
  • GESOP & ASTOS
  • Strengths and weaknesses
varitop
VARITOP
  • “General two-body, sun-centered trajectory design and optimization program”
  • Low thrust trajectories only
chebytop
CHEBYTOP
  • “General two-body, sun-centered trajectory design and optimization program”
  • Computationally quick, but inaccurate
    • Quick mission planning, but future analysis required
midas
MIDAS
  • “Patched-conic interplanetary trajectory solver”
  • Minimizes ΔV and mass, not time
  • Difficult to use, large input files
  • Created to verify the validity of results from other programs
sepspot
SEPSPOT
  • Computes trajectories for electrically propelled spacecraft
  • Considers wide range of forces
  • Only minimizes time
  • Good for Orbital eccentricities less than .65
gesop astos
GESOP & ASTOS
  • “Graphical Environment for Simulation and OPtimization”
  • Can simulate any dynamical system
  • Uses ASTOS application for spacecraft trajectory optimization
  • Requires large amount of input
  • Result accuracy may be affected by broadness of problems it can solve
inspiration
Inspiration
  • Copernicus developed to combine capabilities of other programs,

without their weaknesses

  • Development began Fall 2001 by Dr. Cesar Ocampo
copernicus trajectory system

Ocampo, Cesar, “An Architecture for a Generalized Spacecraft Trajectory Design and Optimization System,” The University of Texas at Austin, Austin, TX, 2003.

Copernicus Trajectory System
  • Goals
    • Solve any type of trajectory problem
      • Initial and final states
        • Fixed or variable
      • Parameters to minimize or maximize
        • Any or all
  • Methods used
    • “Basic” trajectory

segment

the trajectory segment

Ocampo, Cesar, “An Architecture for a Generalized Spacecraft Trajectory Design and Optimization System,” The University of Texas at Austin, Austin, TX, 2003.

The Trajectory Segment
  • Allows boundary conditions to be specified
  • Allows discontinuities
  • Fixed/free parameters
  • Numerical methods used to solve the problem
what it can do
What it can do…
  • 2-body transfer/rendezvous
  • Return trajectories
  • Libration point considerations
  • Low thrust trajectories
  • Gravity assists
  • Ballistic/low energy captures using third-body effects
conclusions
Conclusions
  • General system is necessary
    • Saves mission design time, and man hours
    • Reliable for any conceivable problem
  • Copernicus is the most general trajectory design and optimization system available
    • combines features of other programs without their weaknesses
  • Copernicus is still a prototype, hence there is still a lot to be done – i.e. graphical user interface, OpenGL graphics
references
References
  • For more information about the trajectory systems discussed, see:
    • Ocampo, Cesar, “An Architecture for a Generalized Spacecraft Trajectory Design and Optimization System,” The University of Texas at Austin, Austin, TX, 2003.
    • http://trajectory.grc.nasa.gov/Tools
    • http://www.astos.de