Abstract
The problem of optimal turn of spacecraft as a rigid body of arbitrary dynamic configuration under arbitrary boundary conditions with respect to angular position and angular velocity of spacecraft in the quaternion formulation is considered. The optimality criterion is a functional that combines time and the integral value of the control vector magnitude spent for the spacecraft turn. A special control mode of the spacecraft is studied. Examples of calculations are given.
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.
