The mass of fuel consumed by a rocket to overcome Earth's gravity depends on various factors, including the specific design of the rocket, its payload, and the desired mission trajectory. However, I can provide you with a general idea.
To escape Earth's gravity and reach orbit, rockets need to achieve a velocity known as orbital velocity. This velocity is typically around 28,000 kilometers per hour (17,500 miles per hour). To achieve such high speeds, rockets must carry a significant amount of fuel.
The concept of specific impulse (ISP) is used to measure the efficiency of rocket engines. ISP represents the thrust produced by the rocket engine per unit of fuel consumed. The higher the ISP, the more efficient the engine is in converting fuel into thrust.
Typically, rockets with liquid rocket engines, such as those used in the first stage of many launch vehicles, have specific impulses ranging from a few hundred seconds to over 300 seconds. Solid rocket motors, often used as strap-on boosters or in the initial stages of a rocket launch, tend to have lower specific impulses.
Considering the specific impulse and the desired velocity, rocket engineers calculate the delta-v (change in velocity) required for the mission. Based on the rocket's mass ratio (the ratio of the initial mass to the final mass), they determine the amount of fuel needed.
To give you an example, the Saturn V rocket, which was used for the Apollo moon missions, had a total mass of about 2.8 million kilograms (6.2 million pounds) at liftoff. Approximately 90% of that mass consisted of propellant (fuel and oxidizer). The remaining 10% was the structural mass of the rocket, including the payload, guidance systems, and other components.
Keep in mind that the specific details and fuel requirements can vary significantly depending on the rocket design, mission objectives, and payload characteristics. Rockets used for different missions, such as satellite launches, crewed spaceflights, or interplanetary missions, may have different fuel consumption rates.