Hypervelocity Orbital Intercept Guidance

Abstract

Terminal guidance of a hypervelocity exo-atmospheric orbital interceptor with free end-time is examined. The pursuer is constrained to lateral thrusting with the evader modeled as an ICBM in its final boost phase. Proportional navigation, optimal control using certainty equivalence, dual control, and control with optimum thrust spacing are all examined. Also, a new approach called certainty control is developed for this problem. This algorithm constrains the final state to a function of projected estimate error to reduce control energy expenditure. All methods model the trajectories using splines and employ eight state Extended Kalman Filters with line-of-sight and range updates. The relative effectiveness of these control strategies is illustrated by applying them to various intercept problems.

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Document Details

Document Type
Technical Report
Publication Date
Apr 14, 1988
Accession Number
ADA197149

Entities

People

  • Salvatore Alfano

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Algorithms
  • Boost Phase
  • Computational Science
  • Computer Simulations
  • Equations Of Motion
  • Estimators
  • Filters
  • Guidance
  • Intercontinental Ballistic Missiles
  • Kalman Filters
  • Line Of Sight
  • Mathematical Filters
  • Navigation
  • Nonlinear Systems
  • Proportional Navigation
  • Trajectories

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Missile Defense Systems.

Technology Areas

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