Rocket equation

The rocket equation was proposed by Russian scientist Konstantin Tsiolkovsky in the early 20th century, which revealed the relationship between rocket velocity and propellant mass, exhaust velocity, and initial and final mass of the rocket. The mathematical expression for the rocket equation is: △ V=VeIn (mo/mf) • △ V is the change in rocket velocity, which is the total velocity increment obtained by the rocket. Δ e is the effective exhaust velocity, which is the velocity at which the propellant is ejected after combustion in a rocket engine. M0 is the initial total mass of the rocket, including propellant, structure, payload, etc. MF is the final mass of a rocket, usually referring to the mass after all propellants have been consumed.

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The core content of the Tsiolkovsky rocket equation is: based on the principle of conservation of momentum, any device can generate and obtain acceleration at its original operating speed through a reverse propulsion system that consumes its own mass. Tsiolkovsky's formula: referred to as the "velocity change" by Tsiolkovsky, it refers to the total ability of an aircraft to change its own velocity in an ideal state; It refers to the rate at which gas is ejected backwards from an aircraft - a value now known as the 'specific impulse', which can also be equivalent to the impulse produced per unit mass of propellant per unit time; And are the masses of the aircraft in fully loaded and unloaded states, respectively. Rocket exhaust velocity: the speed at which propellant (fuel+oxidizer) is expelled. Initial mass of rocket: propellant mass+structural mass+payload mass. The final mass of a rocket: initial mass propellant mass. From the Qi equation, we can know that for a rocket, its jet velocity.