USM Space System Lab (USSL) sedang mereka bentuk dan membangunkan MYSat di bawah United Nations/Japan Cooperation Programme on CubeSat Deployment. Subsistem struktur MYSat direka khusus oleh USSL untuk menyokong misi MYSat. Beberapa keperluan CubeSat adalah dikekang oleh pengeluar pelancar CubeSat dan mesti diikuti dalam reka bentuk CubeSat. Dimensi luaran CubeSat mesti serasi dengan pelancar, iaitu J-SSOD dalam kes ini. Selain itu, struktur CubeSat juga perlu menjalani beberapa analisis struktur seperti yang dikehendaki oleh pengeluar J-SSOD, Jepun Aerospace Exploration Agency (JAXA).
Keseimbangan reka bentuk dalam pelbagai aspek telah dijalankan untuk mendapatkan reka bentuk yang optimum untuk subsistem struktur di MYSat. Keseimbangan reka bentuk adalah termasuk pemilihan bahan, casis konsep reka bentuk, kaedah pengancing dan konfigurasi struktur dalaman. Tambahan pula, beberapa analisis struktur dijalankan ke atas casis MYSat dengan menggunakan perisian ANSYS. Analisis adalah termasuk analisis statik struktur, analisis modal dan analisis getaran rawak.
Selain itu, projek ini juga bertanggungjawab untuk pembangunan mekanisme pelepasan antena MYSat. Mekanisme pelepasan wayar terbakar digunakan dalam mekanisme MYSat. Struktur mekanisme ini direka bentuk dan bahan telah dipilih. Fabrikasi mekanisme juga bermula selepas fasa reka bentuk untuk megesahkan reka bentuk. Malangnya, terdapat kelemahan dalam reka bentuk semasa proses fabrikasi. Kecacatan reka bentuk mekanisme dan proses fabrikasi telah dikenal pasti. Oleh itu, beberapa langkah-langkah tindakan untuk mengatasi kelemahan telah dicadangkan.
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USM Space System Lab (USSL) is designing and developing the MYSat under the United Nations/Japan Cooperation Programme on CubeSat Deployment. The structural subsystem of MYSat is specifically designed by USSL to support the mission of MYSat. Numerous requirements of a CubeSat are strictly constrained by the CubeSat deployer manufacturer, which has to be followed in the CubeSat design. The external dimension of the CubeSat must be compatible with the deployer interface, which in this case is the Japanese Experiment Module Small Satellite Orbit Deployer (J-SSOD). Besides, the CubeSat structure must also undergo several structural analysis as required by J-SSOD service provider, Japan Aerospace eXploration Agency (JAXA).
The design trades were done to obtain the optimized the structural subsystem design of MYSat. This trade-off analysis are including material selection, chassis design concept, fastening method and the internal structure configuration. Furthermore, the structural analyses were conducted on the chassis of MYSat by using ANSYS software. The analyses are include static structural analysis, modal analysis and random vibration analysis. The chassis survive all the structural load applied.
This project also studied the development of the antenna deployment mechanism of MYSat. A burn wire release mechanism is utilized in the deployment mechanism. A main plate and revolve ring were designed for the mechanism. Polyether ether ketone (PEEK) was selected as the material for both the parts designed. The fabrication of the mechanism has been done for design verification by applying deployment test. The test result showed the failure of the deployment mechanism. Hence, a few countermeasures to overcome the failure were proposed.
Design and analysis of 1U cubesat structure / Wong Chun Hong