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Dynamic modelling of CubeSat project MOVE
2008 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

In the last few decades the number of small scale satellites has been in an increasing pace. The numbers of market players competing in the global scenario are highly motivated to develop satellites of micro and pico scales, in order to reduce the time frame and project cost.However more complex task have to be performed and even more lifetime and reliability must be provided. The responsibility of an engineer starting from design to delivery (D to D) of a satellite has such an enormous complexity that it can only be solved through team work. The subsystems of a satellite consist of power (EPS), communication (COMM), On board data handling (OBDH), structure, mechanics, thermal, attitude and orbit control (AOCS), telemetry and tracking requires a multidisciplinary approach to achieve within the time span. At the Institute of Astronautics (LRT), Technical University of Munich (TUM), the Space System Concept Centre (S2C2) has been implemented to support the satellite design process, where the CubeSat MOVE is one of the projects under development process. Every work package is handled by different subsystem specialist. Each specialist has their own workstation. The workstations are linked such that all the users can work on the same project. MOVE is an educational project for realization of a CubeSat mission at the Institute of Astronautics. The first satellite �First- MOVE� will verify the satellite platform and new highly efficient solar cells from industry. It is a CubeSat in single-configuration (10x10x10 cm�) which features deployable solar arrays. For support of the development process, the satellite system will be modelled in a system engineering tool ((v)-Sys-ed). Also the system engineering tool can be used to dimension several design parameters like solar array size or battery size. In this thesis an already existing generic model of dimensioning the satellite is used for modelling the project MOVE, while at times the generic models needs to be either updated or changed according to the project requirements and verified with the literature references. The purpose is to keep track of the entire system parameters like mass, energy consumption, and mass memory size and so on. As these models and calculation are only based on a static state of the satellite system, it cannot simulate the dynamic behavior of the satellite, hence it requires dynamic scenarios to be assumed and analyzed. ESA�s SIMVIS tool has been used to validate the link and payload conditions through antenna and payload visibility studies along with visualization. The antenna connectivity to the ground station and the camera visibility with respect to earth are simulated using the SIMVIS tool. Further add to the validation, a similar setup is developed using the predominantly used mission analysis software called AGI Satellite Tool Kit (STK). The latter part of the thesis work is on the implementation of generic dynamic satellite models for the development of one another software called OpenSim Kit. Based on the different software approaches used, the ultimate aim is to compare the software usability and list the expectation of a spacecraft systems engineer.

Place, publisher, year, edition, pages
Keyword [en]
Technology, Dynamic modelling
Keyword [sv]
URN: urn:nbn:se:ltu:diva-58432ISRN: LTU-PB-EX--08/080--SELocal ID: f0377284-582f-4bc7-96a4-3162c3f8aa70OAI: diva2:1031820
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Validerat; 20101217 (root)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

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