🔥 Chemical Thruster Burn Calculator

Burn time · propellant · mass flow · total impulse · finite-burn arc check

Ad placeholder

Inputs

Results

Propellant used
– kg
Mass flow
– g/s
Burn time
–
Total impulse
– N·s
Initial acceleration
– mm/s²
Burn arc
– % of orbit
–
Ad placeholder

📖 How to use

  1. Enter the spacecraft mass, thrust, Isp and this maneuver's Δv (one item of the Δv Budget).输入整星质量、推力、Isp 与本次机动的 Δv（Δv 预算中的一项）。
  2. The burn-arc check flags burns longer than ~5% of the orbit — impulsive assumptions break down and gravity losses grow; split the maneuver or use a bigger thruster.点火弧段检查提示超过轨道周期约 5% 的长点火——脉冲假设失效、引力损失增大；应分次点火或加大推力。
  3. Total impulse across all maneuvers drives thruster qualification (life, pulse count) — sum it over the mission.全任务总冲决定推力器鉴定要求（寿命、脉冲次数）——请对整个任务累加。

Burn relations

Propellant from the rocket equation: m_p = m₀·(1 − e^(−Δv/Isp·g₀)); mass flow ṁ = F/(Isp·g₀); burn time t = m_p/ṁ; total impulse I = F·t = m_p·Isp·g₀.

Finite-burn (gravity) losses stay below ~1% while the burn arc is under a few percent of the orbit; long spiral-like burns should be analyzed as low-thrust transfers instead (see the EP tool).

All computation runs locally in your browser.

点火关系式

由火箭方程 m_p = m₀·(1 − e^(−Δv/Isp·g₀))；质量流量 ṁ = F/(Isp·g₀)；点火时间 t = m_p/ṁ；总冲 I = F·t = m_p·Isp·g₀。

点火弧段在轨道周期百分之几以内时，有限推力（引力）损失通常低于 1%；更长的连续点火应按小推力转移分析（见电推工具）。

全部计算在你的浏览器本地完成。