月球表面近乎真空，月面酬載主要透過結構熱傳導與熱輻射進行熱交換，並可能因月表熱環境隨月球地方時間與緯度變化而面臨操作溫度限制。因此，建立熱分析模型，以評估酬載於月表環境下之溫度反應。 本研究以「外太空探索計畫第一枚月球登陸器」所搭載之月球向量磁場儀（Lunar Vector Magnetometer，LVM）為分析對象，並以磁通閘磁力計（Fluxgate Magnetometer，FGM）作為主要評估元件。研究中使用 SOLIDWORKS 建立 LVM 三維幾何模型，經適當簡化後匯入 Simcenter 3D ，建立有限元素熱分析模型並進行穩態及暫態熱分析。模型考慮各部件之材料熱物性、表面光學性質、資料處理器電子元件熱負載、底板溫度、太陽日照，以及隨月球地方時間變化之環境輻射溫度。 分析首先於月球夜間低溫環境下進行穩態熱分析，並將所得溫度場作為暫態分析之初始條件，再模擬 LVM 於完整月球日之溫度歷時變化。本研究分析緯度 0°、30°、60°、78°、79°、80°及 81°條件下三組 FGM 之溫度反應，並以緯度 80°作為代表案例，呈現 LVM 整體溫度分布及 FGM 溫度歷時。此外，於緯度 80°條件下比較時變與固定環境輻射溫度，以及 FGM 面向東、西、北、南四種安裝配置之影響，並依據 FGM 操作與非操作溫度範圍評估其可運作時段，作為後續 LVM 熱控設計、安裝配置及月表任務操作規劃之參考。;The lunar surface is nearly a vacuum， and lunar payloads exchange heat primarily through structural conduction and thermal radiation. Because the lunar thermal environment varies with lunar local time and latitude， payloads may be subject to operational temperature limitations. Therefore， thermal modeling is necessary to evaluate their temperature responses under lunar surface conditions. This study investigates the Lunar Vector Magnetometer (LVM) carried by the first lunar lander of the Outer Space Exploration Program， with the Fluxgate Magnetometers (FGMs) serving as the primary components of interest. A threedimensional LVM model was developed in SOLIDWORKS， appropriately simplified， and imported into Simcenter 3D to establish a finite element thermal model for steady-state and transient thermal analyses. The model considers the thermophysical and surface optical properties of each component， heat loads generated by the data logger electronics， baseplate temperature， solar illumination， and the radiative environment temperature varying with lunar local time. A steady-state thermal analysis was first conducted under the low-temperature lunar nighttime condition， and the resulting temperature field was used as the initial condition for the transient analysis. The temperature history of the LVM over a complete lunar day was then simulated. The thermal responses of the three FGMs were evaluated at latitudes of 0°， 30°， 60°， 78°， 79°， 80°， and 81°. The 80° latitude case was selected as the representative case to present the overall temperature distribution of the LVM and the temperature histories of the FGMs. In addition， time-varying and constant radiative environment temperature settings， as well as four installation orientations with the FGMs facing east， west， north， and south， were compared at 80° latitude. The allowable operating periods were further evaluated according to the operating and non-operating temperature ranges of the FGMs. The results provide a reference for future LVM thermal control design， installation configuration， and lunar surface mission planning.
