This paper proposes an integrated navigation method based on inertial/starlight combined guidance for the platform single star velocity error correction requirements under certain application environment constraints, in which inertial navigation is the main method and starlight guidance is used to correct initial errors and drift of inertial reference during flight. This paper gives the calculation principle and derivation process of the best star position and the best correction coefficient, and simulates it. At the same time, simulations are also performed when the actual error direction does not agree with the prior information, and when the navigation star deviates from the optimal star position. The simulation results show that the calculation method of the starlight correction coefficient has good adaptability.
Research on Inertial/Star Velocity Error Correction Guidance Method Based on Platform Single Star
Lect. Notes Electrical Eng.
2021-10-30
9 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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