飛鼠號立方衛星之結構次系統;Development, Fabrication, and Test of IDEASSat Structure Subsystem

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Please use this identifier to cite or link to this item: http://ir.lib.ncu.edu.tw/handle/987654321/83310

Title:	飛鼠號立方衛星之結構次系統;Development, Fabrication, and Test of IDEASSat Structure Subsystem
Authors:	劉心慈;Liu, Hsin-Tzu
Contributors:	太空科學與工程研究所
Keywords:	立方衛星;結構次系統;飛鼠號;IDEASSat;3U cubesat
Date:	2020-07-16
Issue Date:	2020-09-02 15:25:30 (UTC+8)
Publisher:	國立中央大學
Abstract:	飛鼠號又稱為(IDEASSAT/INSPIRESAT-2)是一枚3U立方衛星，計畫開始於2017年由國家太空中心(National Space Organization)資助。飛鼠號隸屬於International Satellite Program in Research and Education （INSPIRE）團隊，由國立中央大學(National Central University)負責設計與製作。本文的研究主旨為設計、模擬、製作、組裝飛鼠號的結構次系統。設計方面考慮到飛鼠號的基本規格、結構配置、質心位置、慣性矩、坐標系統、彈射桶選用、材料選用限制等。模擬方面使用SolidWorks Simulation電腦模擬飛鼠號在印度的Polar Satellite Launch Vehicle（PSLV）運載火箭發射以及軌道上運行的過程中會遇到的結構應力與振動，以有限元素分析來建立模型與求解PSLV火箭的環境測試標準，包含自然頻率評估、加速度測試、正弦波振動測試、隨機振動測試、衝擊測試，經過不斷的修改直到結構次系統的設計符合標準。製作方面使用Autodesk Fusion 360 CAM軟體編寫CNC加工機台的G-code，控制加工機台使用指定的刀具進行粗加工與精加工，使用DATRON NEO三軸/四軸CNC高速低溫雕銑機自行精密加工，製作出飛鼠號的外殼結構。組裝方面要確實的按照每個步驟才能完成組裝，依序從電池電路板到S-band電路板，再將CIP連接上來完成結構前半段的組裝，後半段將UHF天線彈射模組、UHF收發機、Sun Sensor、GPS安裝在外殼結構上，組裝ADCS來連結前半段以及後半段的結構，最後安裝太陽能板並且綁上釣魚線來完成所有的組裝程序。;The Ionospheric Dynamics Exploration and Attitude Subsystem Satellite (IDEASSat/ INSPIRESat-2) is a three-unit (U) CubeSat. The project began in 2017 with funding from the National Space Center (NSPO). IDEASSat belongs to the INSPIRE team and is designed by the National Central University of Taiwan (NCU).The main purpose of this paper is to design, simulate, fabricate, and assemble the structure and mechanism sub-system of the IDEASSat. The design of the IDEASSat takes into account the basic specifications , structural configuration, Center of gravity, moment of inertia, coordinate system, deployer selection, material selection restrictions. For simulation, use SolidWorks Simulation to simulate the structural stress and vibration that the IDEASSat will encounter during the launch of the PSLV rocket and during orbital operation. The finite element analysis FEA is used to establish the model and solve the environmental test standards of the PSLV rocket, including resonance survey, acceleration test, sine vibration test, random vibration test, and shock test. The design of the structure and mechanism sub-system is continuously modified until it meets the PSLV rocket standard. In terms of fabrication, Autodesk Fusion 360 CAM software is used to write the programming language G code of the CNC machine, which is used to control the CNC machine to use the specified tools for rough machining and finish machining. Finally, use the DATRON NEO three-axis / four-axis CNC machine to precisely process the shell structure of the IDEASSat. For assembly, we must follow every step to complete the assembly, from the battery circuit board to the S-band circuit board, and then connect the CIP to complete the first half of the structure. In the second half, install the UHF antenna ejection module, UHF transceiver, Sun Sensor, GPS on the shell structure, assemble ADCS to connect the first half and the second half of the structure, and finally install the solar panel and tie the fishing line to complete all the assembly procedures.
Appears in Collections:	[Graduate Institute of Space Science] Department of Earth Sciences

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