Application of an Advanced Trajectory Optimization Method to Ramjet Propelled Missiles

Abstract

The mission performance characteristics of ramjet-propelled missiles are highly dependent upon the trajectory flown. Integration of the trajectory profile with the ramjet propulsion system performance characteristics to achieve optimal missile performance is very complex. Past trajectory optimization methods have been extremely problem dependent and require a high degree of familiarity to achieve success. A general computer code (CTOP) has been applied to ramjet-powered missiles to compute open-loop optimal trajectories. CTOP employs Chebyshev polynomial representations of the states and controls. This allows a transformation of the continuous optimal control problem to one of parameter optimization. With this method, the trajectory boundary conditions are always satisfied. State dynamics and path constraints are enforced via penalty functions. The presented results include solutions to minimum fuel-to-climb, minimum time-to-climb, and minimum time-to-target intercept problems.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1980
Accession Number
ADA113728

Entities

People

  • B. K. Joosten
  • L. E. Fink
  • S. W. Paris

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Altitude
  • Chebyshev Polynomials
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Flight
  • Flight Paths
  • Geometry
  • Intercept Trajectories
  • Mach Number
  • Polynomials
  • Propulsion Systems
  • Simulations
  • Three Dimensional
  • Trajectories
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Missile Defense Systems.
  • Operations Research