Premium
OPTIMAL FEEDBACK GUIDANCE FOR LOW‐THRUST ORBIT INSERTION
Author(s) -
Kluever Craig A.
Publication year - 1995
Publication title -
optimal control applications and methods
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.458
H-Index - 44
eISSN - 1099-1514
pISSN - 0143-2087
DOI - 10.1002/j.1099-1514.1995.tb00012.x
Subject(s) - geosynchronous orbit , orbit (dynamics) , thrust , control theory (sociology) , trajectory , linear quadratic regulator , circular orbit , propulsion , trajectory optimization , aerospace engineering , terminal (telecommunication) , range (aeronautics) , computer science , optimal control , physics , engineering , mathematics , mathematical optimization , telecommunications , satellite , control (management) , classical mechanics , astronomy , artificial intelligence
SUMMARY An optimal feedback guidance scheme is developed for the terminal orbit insertion phase of a low‐thrust planar transfer to geosynchronous orbit. The minimum fuel trajectory between specified energy levels is utilized as a reference trajectory and the guidance law is derived using linear quadratic regulator optimization. The feedback guidance scheme responds effectively to a wide range of initial conditions and results in very precise terminal orbit conditions with near‐optimal performance. The guidance scheme also successfully handles propulsion system uncertainties and extremely large initial state deviations. Numerical results are presented for a variety of orbit insertion manoeuvres.