Abstract
Lambert's problem, as the basis of designing the transfer orbit is reviewed. According to the Lagrange equations, the available range of the transfer time is proposed, then, the improved method for the Lambert's problem and the calculation method of part of the orbital elements basing on the thought of the semi-major axis iterated are obtained. Furthermore, the Newton iteration method is used in solving the semi-major axis, which has improved the computational efficiency. Then, through analyzing the results calculated by the classic Battin-Vaughan's solution and the improved semi-major axis iterated method, the new method is proved efficient and accurate. Finally, the formulas of elliptic orbit, hyperbolic orbit and the parabolic orbit derived from the orbital elements are given.
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.
