Innosat konsep pembangunan, penaksiran risiko, analisa keupayaan daya kebolehtahanan meter-pecut, rate-giro dan pemproses sistem kawalan penentu attitud (ADCS) bagi inertia measurement unit (IMU)

shariff, zulkifli (2007) Innosat konsep pembangunan, penaksiran risiko, analisa keupayaan daya kebolehtahanan meter-pecut, rate-giro dan pemproses sistem kawalan penentu attitud (ADCS) bagi inertia measurement unit (IMU). Masters thesis, Universiti Kebangsaan Malaysia.

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Abstract

The InnoSAT is categorized as a Pico-class/ Cube-class satellite which refer to the small size of the satellite. Commercial satellites although varying in size, usually quite big and weighing in the range of 1000 kg's. InnoSAT satellite is restricted to below 1 kg and size of 10 cm cubes and therefore referred to as a Cubesat. Because of its small size and low weight therefore it was placed in the same launch as secondary payloads. Due to this factor it has no influence on the orbit of satellite will have, its seems that a polar orbit in a height of about 600km is likely and the price of getting the satellite in space is very low compare to the prices of commercial satellite launches. This is a key factor allowing most scientist and engineers of own satellite in spaces for the purpose of testing and terning, analyzing, research and etc. In this project, research and discussion will be given to the conceptual development, risk assessment, reliability and survivability analysis of accelerometer, rate gyro and ADS processor of IMU role by UKM for this InnoSAT program. Overall research and analysis will be focus on Design, Build and Test co-processor unit to acquire measurement from available sensors and perform an experimental ADCS task,develope new and robust algorithms for the determination of Orbit and Attitude information, develope a 3-axis accelerometer sensor and 3-axis rate gyro as the satellite attitude payload, design, built and test co- processor unit to acquire experimental sensors aboard InnoSAT and perform experimental ADCS algorithms,lastly but not least to outline a manufacturing test plan for the sensor board and the coprocessor for flight model.

Item Type: Thesis (Masters)
Uncontrolled Keywords: Scientific satellites,Artificial satellites
Subjects: T Technology > T Technology (General)
T Technology > TL Motor vehicles. Aeronautics. Astronautics
Divisions: Library > Tesis > FTK
Depositing User: Mohd. Nazir Taib
Date Deposited: 30 Nov 2015 02:46
Last Modified: 30 Nov 2015 02:46
URI: http://eprints.utem.edu.my/id/eprint/14848
Statistic Details: View Download Statistic

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