STUDI LINTASAN WAHANA MENUJU BULAN MENGGUNAKAN KONSEP TRANSFER ENERGI RENDAH

• Main Author: Miftahul Falah, Beta
• Format: Final Project
• Language: Indonesia
• Subjects: Astronomi
• Online Access: https://digilib.itb.ac.id/gdl/view/66141
• Institution: Institut Teknologi Bandung

The lack of onboard propellant of the Hiten - Japan spacecraft in 1991 opened a new chapter in constructing a lower energy trajectory of the probe to the Moon. The trajectory designed by Belbruno and Miller provides a schematic transfer to the weak stability boundary region and finally a ballistic capture by the Moon’s gravity. Mathematical modeling in this design allows the vehicle trajectory to be constructed from several segments by utilizing the equilibrium point (Lagrange Point) in the Circular Restricted Three-Body Problem (CRTBP). This work was carried out to examine possible trajectories of the spacecraft from the area around the Earth to the area around the Moon through a numerical survey. In general, the CRTBP in this Final Project is divided into two planar segments (coplanar), namely the CRTBP of the Sun-Earth-spacecraft system and the Earth-Moon-spacecraft system. Distribution of trajectories of the first segment is constructed using an invariant manifolds structure to a Lyapunov orbit around the Lagrange Point 2 (L2) of the Sun-Earth system, which is originated from the area around the Earth. Next, this invariant manifolds structure is headed to a selected Poincare section (a weak stability boundary region). In the second segment, starting from the selected Poincare section another invariant manifolds structure is generated towards a Lyapunov orbit around the L2 of the Earth-Moon system, which is a ballistic capture trajectory. Backward integration method is implemented for all segments. The Final Project accomplishes to obtain the invariant manifolds structures of the Sun-Earth-spacecraft segment and the Earth-Moon-spacecraft segment, to reveal the energy intersection of the system on the Poincare section (a weak stability boundary region) which is a transition doorway between the two segments, and to build an overall design of the Earth-Moon trajectory using low energy concept.