🌬️ Atomic Oxygen Fluence & Erosion Calculator

Ram-surface AO fluence vs altitude · material erosion depth over the mission

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Inputs

Results (ram-facing surface)

AO number density
– m⁻³
Ram flux
– cm⁻²·s⁻¹
Fluence per year
– cm⁻²
Mission fluence
– cm⁻²
Erosion rate
– µm/yr
Mission erosion depth
– µm
–
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📖 How to use

  1. Enter the altitude and material; results apply to ram-facing surfaces — wake surfaces see orders of magnitude less.输入高度与材料；结果针对迎风面——背风面通量低几个量级。
  2. Below ~500 km AO is the dominant material killer: bare kapton, silver interconnects and many polymers need protective coatings (SiO₂) or substitution.约 500 km 以下原子氧是材料的头号威胁：裸聚酰亚胺、银互连与多数聚合物需保护涂层（SiO₂）或换材料。
  3. The verdict compares mission erosion with the film thickness — coatings must survive with margin, and pinhole undercutting makes reality worse than the average.结论将任务期剥蚀量与薄膜厚度对比——涂层需带余量存活，且针孔下切效应使实际情况比平均值更糟。
  4. Densities are mid-solar-activity; VLEO at solar max can be ~3× worse.密度按中等太阳活动取值；超低轨太阳峰年约再恶化 3 倍。

AO erosion model

Ram flux Φ = n_AO · v_orbit; mission fluence F = Φ × time; erosion depth d = F × E_y with the material erosion yield E_y (cm³/atom, kapton = 3.0×10⁻²⁴ by definition of the standard).

Heritage check: ISS-altitude ram kapton erodes tens of µm per year — consistent with LDEF and MISSE flight data. AO also oxidizes silver catastrophically (solar array interconnects) while gold and SiO₂-coated surfaces are essentially immune.

All computation runs locally in your browser.

原子氧剥蚀模型

迎风通量 Φ = n_AO · v_轨道；任务注量 F = Φ × 时间；剥蚀深度 d = F × E_y，E_y 为材料剥蚀率（cm³/原子，聚酰亚胺 = 3.0×10⁻²⁴，为标准基准）。

飞行数据校核：空间站高度迎风面聚酰亚胺每年剥蚀数十微米——与 LDEF、MISSE 试验一致。原子氧对银的氧化是灾难性的（帆板互连片），而金与镀 SiO₂ 表面基本免疫。

全部计算在你的浏览器本地完成。