Advanced Guidance and Autopilot Design for Autonomous Lunar Soft Landing

dc.contributor.guidePadhi, Radhakant
dc.coverage.spatial
dc.creator.researcherBanerjee, Avijit
dc.date.accessioned2022-12-17T10:43:46Z
dc.date.available2022-12-17T10:43:46Z
dc.date.awarded2020
dc.date.completed2020
dc.date.registered
dc.description.abstractAiming towards the development of a long-term lunar research base for scientific exploration of futuristic objectives, soft-landing on the Moon has gained renewed interest worldwide. This work focuses on optimal guidance and autopilot design for multiphase autonomous soft-landing on the lunar surface. The objective of the guidance design is to translate the spacecraft from a parking-orbit towards the designated landing site with a near-zero touchdown velocity. In the process of the development, three different guidance methods that are capable of onboard implementation are explored. In this context, the Model predictive static programming (MPSP) based optimal guidance design has been carried out for the multi-constraint soft-landing mission. The MPSP is a computationally efficient numerical guidance algorithm which requires an initial guess control solution to iterate. In order to obtain a good guess history, an inverse polynomial based explicit guidance is formulated in a nonlinear guidance framework. Next, a minimum jerk based explicit guidance law with a re-targeting feature is proposed for the critical terminal descent phase of soft-landing. Various bottlenecks of existing guidance laws such as guaranteed ground collision avoidance, initial continuity of guidance command in between successive phases, the terminal vertical orientation of spacecraft, and tuning difficulties like time-to-go selection are comprehensively addressed. Formulations of different guidance methods along with detailed simulation studies are presented. The second part of this thesis focuses on autopilot design. In order to realize the guidance command with actuator units, a nonlinear dynamic inversion based autopilot design has been carried out with a six degree of freedom spacecraft model. The spacecraft is composed of two sets of thrust engines as actuator units. The translational motion of spacecraft is driven by primary thrusters which are throttleable...
dc.description.note
dc.format.accompanyingmaterialDVD
dc.format.dimensions
dc.format.extentxxii, 198
dc.identifier.urihttp://hdl.handle.net/10603/426643
dc.languageEnglish
dc.publisher.institutionAerospace Engineering
dc.publisher.placeBangalore
dc.publisher.universityIndian Institute of Science Bangalore
dc.relation
dc.rightsuniversity
dc.source.universityUniversity
dc.subject.keywordEngineering
dc.subject.keywordEngineering Aerospace
dc.subject.keywordEngineering and Technology
dc.titleAdvanced Guidance and Autopilot Design for Autonomous Lunar Soft Landing
dc.title.alternativeAdvanced Guidance and Autopilot Design for Autonomous Lunar Soft-Landing
dc.type.degreePh.D.

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