Abstract
The optimal turn problem of a spacecraft as a solid body with spherical mass distribution for arbitrary boundary conditions with respect to the spacecraft angular position and angular velocity is considered in the quaternion formulation. The functional combining the time and the integral absolute value of the control vector applied for the spacecraft turn is used as the optimality criterion. The special control regime of the spacecraft is studied, the isolated character of this regime is demonstrated. Examples of calculations are presented.
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 callMore From: Journal of Computer and Systems Sciences International
Disclaimer: 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.
