Design and fabrication of test-bed for testing attitude determination of spin stablilized spacecraft.Report as inadecuate




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Luleå University of Technology, Department of Computer Science, Electrical and Space Engineering, Space Technology. (Space Master) 2017 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis

Abstract [en] :  Attitude determination for a spin stabilized satellite is calibrated. A mock spacecraft and a spin simulation test bed are designed and developed. Spin simulation testbed which provides position data is used to acquire true position data. The data from the simulator test bed is used as reference for the sensor data to estimate the error in position of sensor data. Two vector method attitude solutions are used here for attaining the estimated position. Two vectors used for attitude determination are magnetic field vector and sun sensor vector. Calibration of accuracy for sensors is main goal, which is attained by calculating error by comparing the estimated position with true position.

Place, publisher, year, edition, pages: 2017. , 99 p.

National Category : Aerospace Engineering

Identifiers: URN: urn:nbn:se:ltu:diva-62223OAI: oai:DiVA.org:ltu-62223DiVA: diva2:1077742

Subject / course: Student thesis, at least 30 credits

Educational program: Space Engineering, master's level (120 credits)

Presentation : 2017-01-10, 52, JMUW, Wurzburg, 23:07 (English)

Supervisors : Fullmer, Rees, DrUtah State University.

Examiners : Felicetti, Leonard, DrLuleå University of Technology, Department of Computer Science, Electrical and Space Engineering, Space Technology. Available from: 2017-03-07 Created: 2017-02-28 Last updated: 2017-03-07Bibliographically approved



Author: Kudaravalli, Venkata Narayana Chowdary

Source: http://ltu.diva-portal.org/



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