📈 Orbit Transient Temperature Simulator

Lumped-capacity node over two orbits · eclipse swing · thermal time constant

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Node & Orbit

Heat Inputs

Results

Heat capacity C
– kJ/K
Max temperature
– °C
Min temperature
– °C
Swing per orbit
– K
Time constant τ
– min
Steady sunlit / eclipse T
– °C

Temperature over Two Orbits

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📖 How to use

  1. Take the absorbed powers for sunlit and eclipse phases from the Heat Balance tool (its "total heat in" minus internal power), and the eclipse duration from OrbitTools.光照/地影段的吸收功率取自热平衡工具（"总吸热"减去内部功耗），地影时长取自 OrbitTools。
  2. Enter the thermal mass that actually follows the swing — for a fast estimate use the structure + boxes mass, not propellant.热容质量只计实际跟随温度波动的部分——快速估算取结构+单机质量，不含推进剂。
  3. If τ ≫ eclipse duration the node barely feels the eclipse (big spacecraft); if τ ≪ eclipse it swings between the two steady temperatures (thin panels).若 τ ≫ 地影时长，节点几乎感觉不到地影（大卫星）；若 τ ≪ 地影，温度会在两个稳态值之间大幅摆动（薄板）。
  4. Check the swing against component cycling limits; batteries and optics usually set the requirement.将温度波动与设备循环限值对比；通常由蓄电池与光学部件提出最严要求。

Lumped-capacity transient model

One isothermal node with capacity C = m·c_p:

C·dT/dt = Q_abs(t) + Q_int − ε·σ·A·T⁴

integrated through alternating sunlit/eclipse phases. Linearizing about the mean temperature gives the thermal time constant τ = C/(4·ε·σ·A·T̄³) — the single most useful number for judging whether orbit cycling matters.

The model conservatively assumes the whole mass follows one temperature; real spacecraft distribute the swing unevenly (external panels swing most, internal boxes least).

All computation runs locally in your browser.

集总热容瞬态模型

单个等温节点，热容 C = m·c_p：

C·dT/dt = Q_吸收(t) + Q_内 − ε·σ·A·T⁴

在光照/地影交替中积分。围绕平均温度线性化可得热时间常数 τ = C/(4·ε·σ·A·T̄³)——判断轨道周期性温度波动是否重要的最有用指标。

模型保守地假设全部质量同温；真实卫星波动分布不均（外板波动最大，内部单机最小）。

全部计算在你的浏览器本地完成。