Abstract
Different types of local extremals obtained in solving trajectory optimization problems related to space vehicle injection and reentry by applying the Pontryagin’s maximum principle are demonstrated. Some solutions differ qualitatively from traditional ones. It is shown that almost each local extremal revealed provides a global optimum within a certain range of parameter values. The change in the type of the global extremal is, as a rule, of bifurcation nature. Multiplicity of local extremals and significantly nonlinear effects in the behavior of globally optimal solutions are basically caused by the presence of aerodynamic forces which can be sufficiently small as compared with the vehicle weight. Numerical results demonstrate the importance of the study of different types of local extremals at all aerospace vehicle design stages because the implementation of nontraditional optimal control laws can demand changes in the space vehicle configuration.
Sign-in/Register to access full text options 
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.
