Calculadora de Massa de Combustível da Missão
Calcule a massa de combustível necessária para uma missão espacial.
Required Fuel Mass
8,591.41 kg
Required Fuel Mass vs Dry Mass (payload + structure)
Formula
## Mission Fuel Mass From the Tsiolkovsky equation, the fuel needed for a given delta-v depends exponentially on the ratio dv/ve. ### Formula **m_fuel = m_dry * (exp(dv / ve) - 1)** - *m_dry* = payload plus structural mass - *dv* = required velocity change - *ve* = exhaust velocity This shows why high delta-v missions are so demanding on fuel.
Exemplo Resolvido
5000 kg dry mass, 3000 m/s delta-v, 3000 m/s exhaust velocity.
- 01m_fuel = m_dry * (exp(dv/ve) - 1)
- 02dv/ve = 3000/3000 = 1
- 03exp(1) = 2.7183
- 04m_fuel = 5000 * (2.7183 - 1) = 5000 * 1.7183
- 05m_fuel = 8591 kg
Perguntas Frequentes
How does this change with multiple stages?
Each stage is calculated independently. The payload of one stage becomes the total mass of the next, compounding the savings from discarding empty tanks.
Why does fuel mass grow exponentially?
The rocket must carry fuel to accelerate the remaining fuel. This feedback loop leads to exponential growth with delta-v.
What is a typical fuel fraction for orbital launch?
About 85% to 92% of the launch mass is propellant. Only 1-4% is payload for a single-stage system.