Abstract
Return orbit design and characteristic analysis are very important issues in manned lunar missions. In this paper, a three-impulse return orbit scheme is studied. First, a convenient method based on the conical surface of the hyperbolic excess velocity is proposed, which can effectively perform an approximate analysis of the velocity increment characteristic. Second, a serial orbit design strategy is presented to determine the entire return orbit from the lunar parking orbit to the intended landing site. In the initial design, a three-segment orbit patched method based on the pseudo-perilune parameters is applied. Backward and forward calculations are conducted in the hybrid orbit model and the patched-conic model respectively, with the perilune of the lunar escape orbit as the dividing point. In the accurate design, a two-segment orbit patched method is employed in the high-fidelity model. Finally, numerical simulations are used to verify the effectiveness and feasibility of the orbit design strategy. According to many simulation results achieved by this strategy, the characteristics of fixed-point return window and velocity increment are further analyzed.
Highlights
Many countries are focusing on manned deep space exploration, and the moon is regarded as the goal [1]
We propose the conical surface of the hyperbolic excess velocity and establish a convenient model as a preliminary analysis tool for the velocity increment characteristic analysis of three-impulse return orbit
Aiming at manned lunar return missions intended for highlatitude regions, a return orbit scheme of the three-impulse maneuver is studied
Summary
Many countries are focusing on manned deep space exploration, and the moon is regarded as the goal [1]. Russia is expected to complete its first manned lunar landing in 2031 and begin the establishment of the first lunar base [3]. With the success of the “Chang’E-4” mission [6]-[7], increasingly people are looking forward to realizing a Chinese manned lunar landing as soon as possible [8]. The lunar landing areas of the early American Apollo missions were mainly concentrated near the lunar equator. Manned lunar missions are large systematic projects, of which the orbit scheme is an important component. As one of the requirements of the manned lunar landing, the spacecraft must have the capability to safely return to the intended landing site from any lunar parking orbit at any time in case the mission fails and must be aborted
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
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.