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. (rrh)
Hypervelocity Orbital Intercept Guidance
1988
186 pages
Report
Keine Angabe
Englisch
Antimissile Defense Systems , Missile Guidance & Control Systems , Interceptors , Proportional navigation , Terminal guidance , Algorithms , Boost phase , Control , Energy consumption , Errors , Estimates , Exosphere , Guidance , Guided missiles , Hypersonic velocity , Interception , Kalman filtering , Long range(Distance) , Models , Optimization , Orbits , Strategy , Thrust , Trajectories
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