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The elaboration of some subsystems of a meteorological satellite/Mohd Khairul Azwade Ab Aziz

The elaboration of some subsystems of a meteorological satellite_Mohd Khairul Azwade Ab Aziz_A2_2011_NI
Kajian ini membincangkan penyediaan sistem – sistem bagi sebuah kapal angkasa iaitu satelit dengan menganalisa dan mereka bentuk beberapa sistem tersebut. Sistem – sistem tersebut termasuklah, Sub-Sistem Bekalan Kuasa Elektrik, Sistem Kawalan Persekitaran, Sub-Sistem Struktur dan Mekanisma kapal angkasa dan beberapa lagi. Dalam Sub-Sistem Bekalan Kuasa Elektrik, ia melihat bagaimana ia boleh menghasilkan tenaga elektrik yang mencukupi kepada satelit semasa perpindahan orbit dan juga sepanjang satelit itu beroperasi. Pada kedudukan orbit geo- pegun Bumi (GEO), tenaga elektrik boleh diperoleh melalui cahaya matahari dengan menukarkannya kepada tenaga elektrik. Namun pada waktu ketiadaan cahaya, tenaga elektrik hanya boleh dibekalkan melalui bateri yang dibawa bersama satelit itu. Waktu ketiadaan matahari atau gerhana dikira bertujuan untuk mengetahui tempoh yang diperlukan untuk bateri beroperasi. Bagi mengatasi keadaan persekitaran yang melampau di angkasa lepas, suatu sistem kawalan haba atau persekitaran adalah perlu supaya satelit itu dapat beroperasi dengan baik. Oleh itu, peralatan kawalan haba yang sesuai dengan misi angkasa perlu disediakan dengan betul. Orbit perpindahan ‘Non- Coplanar Hohmann Transfer’ digunakan terutama bagi satelit goe-pegun Bumi (GEO) kerana tempoh masa dan penggunaan tenaga yang kurang berbanding jenis – jenis perpindahan orbit yang lain. Penggunaan perpindahan orbit ini adalah bagi menempatkan satelit dari orbit sokongan ke orbit bekerja satelit itu di mana di dalam kes ini adalah orbit geo-pegun Bumi (GEO). Perbandingan dilakukan di antara beberapa lokasi pelancaran bagi menentukan perbezaan tempoh penerbangan satelit ke orbit yang ditetapkan. ______________________________________________________________________________________ This project describes the preparation of the subsystems for a spacecraft, which is satellite by analyzing and then designing some of the systems. The subsystems consist of Electrical Power Control Subsystem, Thermal Control Subsystem, Structure and Mechanism Subsystem of the spacecraft and a few others. In the Electrical Power Subsystem, it considers how it can produce enough electrical power to the satellite while in the transfer process and also in the time the satellite operate. In Geostationary Earth Orbit (GEO) electrical power can be regulated from the sunlight by converting it into the electrical power. However, at the time of eclipse, the electrical power can only be by the battery brought along with the satellite. The time of eclipse must be calculated to determine the period that need for the battery to operate. To overcome the harsh space environment, a thermal control system is necessary so that the satellite could operate well. Therefore, suitable thermal control equipment must be provided correctly. The ‘Non-Coplanar Hohmann Transfer’ used especially for the Geostationary Earth Orbit (GEO) because of the short transfer period and low energy consumption proportionate with other types of orbit transfer. The application of this orbit transfer is to locate the satellite from supporting orbit to the working orbit where in this case, the Geostationary orbit (GEO). The comparison between some launch locations for the transfer must be done to determine the transfer period for the satellite flight trough the set orbit.
Contributor(s):
Mohd Khairul Azwade Ab Aziz - Author
Primary Item Type:
Final Year Project
Language:
English
Subject Keywords:
spacecraft ; Coplanar Hohmann Transfer’ ; subsystems
First presented to the public:
5/1/2011
Original Publication Date:
8/1/2019
Previously Published By:
Universiti Sains Malaysia
Place Of Publication:
School of Aerospace Engineering
Citation:
Extents:
Number of Pages - 136
License Grantor / Date Granted:
  / ( View License )
Date Deposited
2019-08-01 11:30:39.814
Submitter:
Nor Hayati Ismail

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