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A rocket's required mass ratio as a function of effective exhaust velocity ratio. The classical rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that follow the basic principle of a rocket: a device that can apply acceleration to itself using thrust by expelling part of its mass with high velocity and can thereby move due to the ...
A Single-Stage-to-Orbit Thought Experiment Archived 15 June 2021 at the Wayback Machine; Why are launch costs so high?, an analysis of space launch costs, with a section critiquing SSTO; The Cold Equations Of Spaceflight A critique of SSTO by Jeffrey F. Bell. Burnout Velocity Vb of a Single 1-Stage Rocket
Rocket mass ratios versus final velocity calculated from the rocket equation. The Tsiolkovsky rocket equation, or ideal rocket equation, can be useful for analysis of maneuvers by vehicles using rocket propulsion. [2] A rocket applies acceleration to itself (a thrust) by expelling part of its mass at high speed. The rocket itself moves due to ...
The velocity and altitude of the rocket after burnout can be easily modeled using the basic physics equations of motion. When comparing one rocket with another, it is impractical to directly compare the rocket's certain trait with the same trait of another because their individual attributes are often not independent of one another.
Rocket mass ratios versus final velocity calculated from the rocket equation Main article: Tsiolkovsky rocket equation The ideal rocket equation , or the Tsiolkovsky rocket equation, can be used to study the motion of vehicles that behave like a rocket (where a body accelerates itself by ejecting part of its mass, a propellant , with high speed).
Velocity at burnout was approximately 5,000 feet (1,500 m) per second. The rocket would typically have a small, unpredictable angular momentum at burnout causing unpredictable roll with pitch or yaw as it coasted upward approximately 75 miles (121 km). A typical flight provided an observation window of 5 minutes at altitudes above 35 miles (56 km).
In rockets, the total velocity change can be calculated (using the Tsiolkovsky rocket equation) as follows: = (+) Where: v = ship velocity. u = exhaust velocity. M = ship mass, not including the working mass. m = total mass ejected from the ship (working mass).
The boost phase is the portion of the flight of a ballistic missile or space vehicle during which the booster and sustainer engines operate until it reaches peak velocity. . This phase can take 3 to 4 minutes for a solid rocket (shorter for a liquid-propellant rocket), the altitude at the end of this phase is 150–200 km, and the typical burn-out speed is 7 k