Abstract
To transport payload into lunar transfer orbit using spinning tether system, reusable payload transport design were proposed and analysed. When final design was decided, open-loop reference control of payload transport stage was developed using optimal control theories. For the insufficient thrust case in LEO orbit, Hamiltonian on/off control was used to solve the problem. Numerical results indicate that the final transport design is able to transport payload into desired orbit, and the control law could satisfy mission requirement. Compared to conventional rocket transport, much less propellant is required by the spinning system with system reusability.
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: International Journal of Space Science and Engineering
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.
