⚖️ Propellant Mass Calculator

Tsiolkovsky rocket equation · propellant from Δv, Isp and dry/wet mass

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Inputs

Results

Exhaust velocity
– km/s
Mass ratio
–
Propellant mass
– kg
Dry mass
– kg
Wet mass
– kg
Propellant fraction
– %
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📖 How to use

  1. Bring the margined Δv from the Δv Budget tool and pick the propellant type — Isp auto-fills.带入 Δv 预算工具的含余量 Δv,选推进剂类型——Isp 自动填入。
  2. Choose whether you know the dry mass (bottom-up build) or the wet mass (launcher-limited) — the tool solves the other.选择已知干重(自下而上估算)还是湿重(受运载约束)——工具反解另一个。
  3. Note the Isp leverage: the same 176 m/s costs a 200-kg sat ~15 kg of hydrazine but only ~2 kg of xenon on a Hall thruster.注意 Isp 的杠杆:同样 176 m/s,200 kg 卫星用肼约需 15 kg,用霍尔电推只需约 2 kg 氙。
  4. Continue to Tank Sizing for volume and to Mass Budget to roll the propellant into the wet mass.接着用贮箱容积算体积,用质量预算把推进剂并入湿重。

The rocket equation

Δv = Isp·g₀·ln(m_wet/m_dry)   ⇒   m_p = m_dry·(e^(Δv/Isp·g₀) − 1)

g₀ = 9.80665 m/s². The exponential means propellant fraction explodes with Δv/(Isp·g₀): chemical propulsion is fine for hundreds of m/s, while km/s-class missions on small sats push you to electric propulsion — at the price of power (see the EP tool) and thrusting time.

All computation runs locally in your browser.

火箭方程

Δv = Isp·g₀·ln(m_湿/m_干)   ⇒   m_p = m_干·(e^(Δv/Isp·g₀) − 1)

g₀ = 9.80665 m/s²。指数关系意味着推进剂比例随 Δv/(Isp·g₀) 急剧增长:数百 m/s 用化学推进即可,小卫星上 km/s 量级的任务则倒向电推进——代价是功率(见电推工具)与点火时长。

全部计算在你的浏览器本地完成。