太空天氣探測儀（SWIP）為福衛九號首顆衛星所搭載之科學酬載，由小型電離層探測儀（CIP）與電子溫度密度探測器（TeNeP）所組成，構成一具雙儀器整合的科學酬載。為因應酬載機構空間的限制，需有效整合各系統，尤其在結構次系統的設計上，面臨相較以往更具挑戰性的雙酬載配置。 本論文以「設計－模擬－實測」為主軸，遵循系統工程流程，從任務需求與任務定義出發，發展初步概念設計，逐步建立太空天氣探測儀之初步機構設計。隨後，依據太空中心所制定之環境試驗規範，進行機構與熱模擬分析，並完成振動測試驗證。根據初步模擬與實測結果進行細部設計修正後，再次執行細部機構與熱模擬，以驗證設計最終可行性與可靠度，確保酬載於太空環境下之機構與熱控次系統能穩定運作。 ;The Space Weather Ionospheric Payload （SWIP） is the scientific payload onboard Taiwan’s FORMOSAT-9A （FS-9A） satellite. It integrates two instruments: the Compact Ionospheric Probe （CIP） and the Electron Temperature and Density Probe （TeNeP）, forming a dual-function, integrated payload system. Due to the constrained payload volume and platform, efficient integration of all subsystems is required, posing significant challenges in the structural design of this dual-instrument configuration. This thesis adopts a design–simulation–verification approach within a systems engineering framework. Starting from mission requirements and definition, a conceptual design was developed to establish the initial structural configuration of SWIP. Structural and thermal analyses were performed based on the environmental test conditions specified by the Taiwan Space Agency （TASA）, followed by vibration test verification. Based on the preliminary simulation and test results, design refinements were implemented, and detailed simulations were carried out to validate the final structural and thermal design. This process ensures that the payload’s structural and thermal subsystems can function reliably in the space environment.
