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Advanced Rocket Propulsion Stanford University • Combine the definitions of the thrust coefficient and c* to express the thrust • Think of nozzle as a thrust amplifier and C F as the gain • Specific Impulse: Thrust per unit mass expelled • Impulse Density: Thrust per unit volume of propellant expelled
The term T = c dm/dt is called the thrust of the rocket and can be interpreted as an additional force on the rocket due to the gas expulsion. Equation (12) is a vector equation which can be projected along the direction of v (tangent to the path).
This resource contains informations about rocket thrust, momentum balance, thrust equation, jet power and Stagnation Enthalpy.
• Derived the rocket equation (1903) • Introduced multi stage rockets (1924) – He has laid the mathematical foundation of modern space flight • Identified exhaust velocity as an important parameter – Understood the importance of high temperature and low molecular weight in obtaining high exhaust velocities
The Rocket Equation. We consider a rocket of mass m, moving at velocity v and subject to external forces F (typically gravity and drag). The rocket mass changes at a rate ̇m = dm/dt, with a velocity c relative to the rocket. We shall assume that the magnitude of c is constant.
This means that it can operate in any part of the atmosphere and outside 2 the atmosphere which makes it ideal for space propulsion. The thrust is produced because the rocket engine must have exerted a force on exhaust material and an equal and opposite force, the thrust, therefore, exerted on the rocket.
The rocket equation 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 …
