Abstract
AbstractThis paper presents an analytical zero-effort-miss (ZEM)/zero-effort-velocity (ZEV) feedback guidance algorithm using the Levi-Civita transformation, where the ZEM and ZEV vectors can be determined explicitly instead of numerical integration or any propagators. In each guidance cycle, the states of the spacecraft and target are first transformed into Levi-Civita coordinate, the optimal time-to-go is then computed through the Newton–Raphson method and the ZEM/ZEV vectors are determined explicitly, the optimal control inputs are finally transformed back into cartesian coordinate. The effectiveness of the proposed method is demonstrated using a missile intercept and a head-on collision intercept problem.KeywordsZEM/ZEV guidanceLevi-Civita transformationOptimal time-to-go
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
