Study and Design of an Adaptive Control Law for Spacecraft Attitude Control
Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
In this thesis the problem of spacecraft attitude control is investigated. The spacecraft dynamics are modeled as a rigid body system controlled by 4 thrusters, and the kinematics are represented by direction cosine matrix. In this thesis, the effectiveness of retrospective cost adaptive control for spacecraft attitude control is evaluated. The prominent feature of this adaptive controller is that it requires little knowledge of the system to be controlled. This makes this controller attractive since for most spacecraft knowledge of the spacecraft’s inertia tensor is limited and will sometimes change over the spacecraft lifetime.
Place, publisher, year, edition, pages
2014. , 60 p.
Technology, Adaptive Control, RCAC, Attitude Control, ADCS, AOCS, Spacecraft
IdentifiersURN: urn:nbn:se:ltu:diva-50766Local ID: 7fe41f8d-9900-4350-82b9-4ffc006c6064OAI: oai:DiVA.org:ltu-50766DiVA: diva2:1024128
Subject / course
Student thesis, at least 30 credits
Space Engineering, master's level
Hromcik, MartinS. Bernstein, Dennis
Validerat; 20140728 (global_studentproject_submitter)2016-10-042016-10-04Bibliographically approved