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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
• 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.
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.
Rocket propulsion harnesses Newton's third law, expelling mass to generate thrust. This chapter dives into the fundamentals, exploring propellant types, engine efficiency, and the critical thrust equation that governs rocket performance.
• Rocket Motors Forces on the Rocket Equation of Motion: ∑F = Ma Center of Mass Forces at through the Center of Mass (1) Gravity: F Grav = Mg F Grav (2) Thrust: F Thrust = (MV) dt d F Thrust The thrust force seen by the rocket is equal to the rate of change of momentum carried away in the exhaust Need to minimize total mass M to maximize ...
