Development Of Mysat (1u Cubesat) Mission Analysis And Design

Thaheer, Ahmad Shaqeer Mohamed (2018) Development Of Mysat (1u Cubesat) Mission Analysis And Design. Masters thesis, Universiti Sains Malaysia.

Preview

PDF Download (267kB) | Preview

Abstract

Platform angkasa berkos rendah diperlukan untuk mengukur ketumpatan elektron di ruang Ionosfera untuk membuktikan hubungan anomali bumi dan perubahan ketumpatan elektron. Kaedah pengukuran terdahulu dilakukan menggunakan satelit traditional yg sangat mahal dan bersaiz besar. Namun, pembangunan satelit adalah rumit kerana komponen dipilih perlu optimal dan dilaksanakan untuk misi itu. Analisis reka bentuk awal dilakukan untuk menentukan keperluan sesuai untuk misi dan setiap subsistem. Oleh itu, kajian ini membentangkan analisis misi dan reka bentuk struktur dan analisis 1U Satelit Kiub dinamakan MYSat. MYSat dijangka dilancarkan menggunakan JEM Small Satellite Orbital Deployer (J-SSOD) di Stesen Angkasa Antarabangsa (ISS) dengan misi mengukur ketumpatan elektron di Ionosfera. Kajian bermula dengan definisi misi melalui menyenaraikan objektif dan keperluan misi dan subsistem. Seterusnya, analisis orbit MYSat dilakukan mengunakan perisian Systems Tool Kit (STK) untuk mengira jangka hayat orbit. Simulasi ini juga dilakukan untuk menentukan masa pengcahayaan dan jejak bumi MYSat. Hasil simulasi dan konsep operasi itu dimasukkan ke keperluan subsistem dan bajet awal subsistem dikira. Struktur MYSat juga direka dan analisis struktur dilakukan mengunakan perisian ANSYS. MYSat akan mengorbit pada altitud 400 km dengan jangkaan hayat 1 ke 1.3 tahun. Ia tidak mempunyai kawalan tingkah laku dan dilengkapi dengan sistem kawalan therma pasif. Jaringan komunikasi menggunakan Penerima Frekuensi Sangat Tinggi (VHF) (114-146 MHz), dan Pemancar Frekuensi Ultra Tinggi (UHF) (435-438 MHz) dengan kuasa pancaran terhad kepada 1.5 W. Sel solar GaAs (UTJ) digunakan untuk penjanaan kuasa dilengkapi bateri Li-ion. Semua subsistem termasuk unit sains Prob Suhu dan Ketumpatan Elecktron (TeNeP) telah diintegrasikan ke dalam struktur bersaiz 10×10×11.35 cm dengan berat maksimum 1.30 kg. Hasil kajian menunjukan rekaan dibangunkan boleh dilaksanakan dan beroperasi dengan cekap menggunakan kuasa dan berat tersedia. Hasil analisis struktur menunjukkan purata tekanan di alami oleh MYSat adalah di bawah kekuatan akhir bahan itu. Oleh itu, struktur itu mampu menampung keadaan tekanan yang melampau. Analisis itu juga menunjukkan nombor ballistik dan frekuensi semula jadi MYSat mengikut kehendak system pelancaran J-SSOD. Kaedah yang digunakan adalah berkesan dalam menganggar keputusan awal, tetapi sekumpulan ahli pakar disyorkan untuk projek ini kerana ia melibatkan bidang berlainan; Oleh itu, analisis yang lebih terperinci dapat dilakukan untuk meningkatkan pembangunan MYSat untuk misi untuk berjaya. _______________________________________________________________________________________________________ A low-cost space platform is needed in measuring the electron-density in the ionosphere to prove the correlation between earth anomalies and the changes of the electron-density. The previous method of measurement is done using traditional satellite, which is very costly and huge. However, satellite development has been a complicated process as the components chosen should be optimized and feasible for the mission. Thus, a preliminary design analysis is done to determine the requirement that suits for the mission and each subsystem. Therefore, this research presents a mission analysis and structure design and analysis of 1U CubeSat named MYSat. MYSat is expected to be deployed using JEM Small Satellite Orbital Deployer (J-SSOD) at the International Space Station (ISS) with a mission of measuring the electron-density in Ionosphere. The research started with mission definition by deriving the objectives and requirements of the mission and subsystems. Then, the orbital analysis is then conducted using Systems Tool Kit (STK) software to estimate the orbital lifetime. The simulation performed is also to determine lighting time and ground track of MYSat. The result from the simulation and operational concept become the input for subsystem’s requirement, and initial subsystem budget is calculated. The structure of MYSat has been designed and structural analysis has been performed using ANSYS software. MYSat is orbiting about 400 km in altitude with the expected lifetime of 1 to 1.3 years. It does not have an attitude control and uses a passive thermal control. The communication link uses Very-High Frequency (VHF) Receiver (144-146 MHz), and Ultra-High Frequency (UHF) Transmitter (435-438 MHz) with limited transmission power of 1.5 W. GaAs (UTJ) solar cell is used for power generation with a Li-ion battery as power storage. All the subsystems including Temperature and Electron-density Probe (TeNeP) science unit are integrated into a 10×10×11.35 cm structure with a maximum mass of 1.30 kg. The results show that the design is feasible and that the mission could efficiently work with the available power and mass. The result of structural analysis also demonstrated that the average stress that MYSat experienced is well below the material’s ultimate strength. Thus, the structure can withstand harsh loading conditions during the mission. It also shows that MYSat ballistic number and natural frequency are following the requirements defined by J-SSOD launch system. The methods used was effective in estimating the preliminary results, but a group of expert teams is recommended for this project as it involves different background fields; hence, a more detail analysis can be done to improve MYSat development for the mission to be successful.

Item Type:	Thesis (Masters)
Additional Information:	Full text is available at http://irplus.eng.usm.my:8080/ir_plus/institutionalPublicationPublicView.action?institutionalItemId=4686
Subjects:	T Technology T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL787-4050 Astronautics. Space travel
Divisions:	Kampus Kejuruteraan (Engineering Campus) > Pusat Pengajian Kejuruteraan Aeroangkasa (School of Aerospace Engineering) > Thesis
Depositing User:	Mr Mohd Jasnizam Mohd Salleh
Date Deposited:	12 Jun 2019 09:00
Last Modified:	12 Jun 2019 09:00
URI:	http://eprints.usm.my/id/eprint/44569

Actions (login required)

View Item