Accession Number : ADA197149


Title :   Hypervelocity Orbital Intercept Guidance


Descriptive Note : Doctoral thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH


Personal Author(s) : Alfano, Salvatore


Full Text : http://www.dtic.mil/get-tr-doc/pdf?AD=ADA197149


Report Date : 14 APR 1988


Pagination or Media Count : 185


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.


Descriptors :   *INTERCEPTORS , *PROPORTIONAL NAVIGATION , *TERMINAL GUIDANCE , ALGORITHMS , GUIDED MISSILES , CONTROL , ORBITS , OPTIMIZATION , STRATEGY , BOOST PHASE , TRAJECTORIES , THRUST , ENERGY CONSUMPTION , HYPERSONIC VELOCITY , EXOSPHERE , MODELS , INTERCEPTION , KALMAN FILTERING , ESTIMATES , LONG RANGE(DISTANCE) , ERRORS , GUIDANCE.


Subject Categories : GUIDED MUNITIONS
      SPACECRAFT TRAJECTORIES AND REENTRY


Distribution Statement : APPROVED FOR PUBLIC RELEASE