🔥 Spacecraft Heater Sizing Calculator

Cold-case losses at the setpoint · heater power with margin · duty cycle & orbit energy

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Component & Losses

Results

Conductive loss
– W
Radiative loss
– W
Net loss (− dissipation)
– W
Heater power (with margin)
– W
Duty cycle at that rating
– %
Energy per orbit
– Wh
–
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📖 How to use

  1. Enter the setpoint and the cold-case mounting/sink temperatures; get G from the Conduction tool and ε*·A from the MLI tool for wrapped components.输入控温点与冷工况的安装面/热沉温度；G 用导热耦合工具计算，包覆件的 ε*·A 用 MLI 工具计算。
  2. The heater must cover conductive + radiative losses minus the component's own standby dissipation, with 25% margin per usual practice.加热器需覆盖导热+辐射漏热减去部件自身待机功耗，按惯例加 25% 余量。
  3. The installed rating runs at the reported duty cycle under thermostat control; energy per orbit feeds the EPS power budget (eclipse-phase load).装机功率在恒温器控制下按所示占空比工作；每圈能量应计入电源功率预算（阴影段负载）。
  4. Batteries, propellant lines and optics are the usual heater customers — check their limits on the Reference page.蓄电池、推进管路与光学部件是加热器的常客——温度限值见参考页。

Heater sizing relations

Holding a component at T_set in the cold case requires

Q_htr = [G·(T_set − T_mount) + ε·σ·A·(T_set⁴ − T_sink⁴) − Q_int] × (1+margin)

Thermostatic heaters are installed above the worst-case need and cycle at duty = need/rating. Undersized couplings (small G, good MLI) are the cheapest heater power you will ever buy — isolate first, heat second.

All computation runs locally in your browser.

加热器设计关系式

冷工况下把部件维持在 T_set 需要

Q_加热 = [G·(T_set − T_安装) + ε·σ·A·(T_set⁴ − T_沉⁴) − Q_内] × (1+余量)

恒温加热器按最恶劣需求放大装机，实际以占空比 = 需求/装机 循环工作。减小耦合（小 G、好 MLI）是最便宜的"加热功率"——先隔热，后加热。

全部计算在你的浏览器本地完成。