🧾 Satellite Δv Budget Calculator

Itemized mission Δv · margin · the sizing input for propellant & tanks

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Δv Items

One row per maneuver class over the whole mission. Blank/zero rows are ignored. Get individual values from OrbitTools (maneuver, lifetime drag make-up).

每类机动一行，取整个任务寿命的总量。留空/为 0 忽略。单项数值可用 OrbitTools 计算（机动、寿命工具的阻力补偿）。

ManeuverΔv (m/s)Share

Margin

Results

Subtotal
– m/s
Total with margin
– m/s
Largest item
–
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📖 How to use

  1. List every maneuver class for the whole mission: injection correction, phasing/acquisition, drag make-up × years, station keeping × years, collision avoidance, disposal/deorbit.逐项列出全寿命各类机动：入轨修正、初始调相、阻力补偿×年数、位置保持×年数、碰撞规避、离轨处置。
  2. Pull numbers from OrbitTools: the maneuver tool for transfers/phasing, the lifetime tool for drag make-up per year.数值取自 OrbitTools：转移/调相用机动工具，每年阻力补偿用寿命工具。
  3. Typical margins are 5–15%; early phases and drag-driven missions take the high end.余量通常 5–15%；方案早期与阻力主导的任务取高值。
  4. Carry the margined total into the Propellant Mass tool.把含余量总 Δv 带入推进剂质量工具。

Typical mission Δv values

LEO smallsat (5 yr, 500 km): injection correction 10–20, phasing 5–15, drag make-up 2–20/yr (altitude!), collision avoidance ~5, controlled deorbit 80–150 m/s.

GEO (15 yr): GTO circularization ≈ 1500 (usually the apogee engine's job), N-S station keeping ≈ 50/yr, E-W ≈ 2/yr, graveyard re-orbit ≈ 11 m/s.

VLEO missions are dominated by continuous drag make-up — hundreds of m/s per year below 300 km; electric propulsion is almost mandatory there.

All computation runs locally in your browser.

典型任务 Δv 取值

LEO 小卫星（5 年，500 km）：入轨修正 10–20、初始调相 5–15、阻力补偿每年 2–20（强烈依赖高度）、碰撞规避约 5、受控离轨 80–150 m/s。

GEO（15 年）：GTO 圆化约 1500（通常由远地点发动机承担）、南北位保约 50/年、东西位保约 2/年、坟墓轨道抬升约 11 m/s。

超低轨任务由连续阻力补偿主导——300 km 以下每年可达数百 m/s，基本必须用电推进。

全部计算在你的浏览器本地完成。