🔋 Spacecraft Battery Sizing Calculator

Required capacity · series/parallel cell layout · mass · recharge power

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Load & Requirements

Chemistry & Cells

Results

Energy per eclipse
– Wh
Required capacity
– Wh
Required capacity
– Ah
Cells in series
– S
Parallel strings
– P
Installed capacity
– Wh
Actual DoD
– %
Battery mass
– kg
Avg discharge current
– A
Recharge power needed
– W
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📖 How to use

  1. Bring the eclipse load (with margin) and the year's longest eclipse; set the max DoD from the Cycle Life tool.带入含余量的阴影负载与全年最长阴影时长；最大 DoD 取自循环寿命工具。
  2. Pick the chemistry — cell voltage and specific energy auto-fill; adjust cell capacity to your candidate cell (e.g. 10 Ah space Li-ion).选择电化学体系——单体电压与比能量自动填入；单体容量按备选电芯修改（如 10 Ah 宇航锂电）。
  3. Read the S/P layout, installed capacity, actual DoD and mass; N+1 keeps DoD legal with one string failed.读取串并联配置、装机容量、实际 DoD 与质量；N+1 保证单串失效后 DoD 仍不超限。
  4. The recharge power must be covered by array surplus in sunlight — verify in the Orbit Energy Balance tool.光照期帆板富余功率必须覆盖回充功率——用能量平衡工具校核。

Battery sizing equations

Required capacity: C = P_e·T_e / (DoD·η_dis) — the eclipse energy divided by allowed depth of discharge and the discharge path efficiency.

Cell layout: series cells N_s = ceil(V_bus/V_cell); parallel strings N_p = ceil(C_Ah/C_cell) (+1 if string-out redundancy). Installed capacity = N_s·N_p·V_cell·C_cell.

Recharge: returning the discharged energy with ~10% overcharge in the available sunlight: P_chg = 1.1·E_dis/(η_chg·T_chg) (η_chg ≈ 0.9 folded in).

Typical DoD limits: Li-ion LEO 20–30%, GEO 60–80%; NiH₂ LEO 40%, GEO 80%. See the Cycle Life tool.

All computation runs locally in your browser.

蓄电池设计公式

所需容量: C = P_e·T_e / (DoD·η_放) —— 阴影能量除以允许放电深度与放电路径效率。

电芯配置: 串联数 N_s = ceil(V_bus/V_cell)；并联串数 N_p = ceil(C_Ah/C_cell)（选串冗余时 +1）。装机容量 = N_s·N_p·V_cell·C_cell。

回充: 在可用光照时间内以约 10% 过充返还放出能量：P_充 = 1.1·E_放/(η_充·T_充)（η_充 ≈ 0.9 已计入）。

典型 DoD 限值：锂离子 LEO 20–30%、GEO 60–80%；氢镍 LEO 40%、GEO 80%。详见循环寿命工具。

全部计算在你的浏览器本地完成。