User:Milton Beychok/Sandbox: Difference between revisions
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:<math>F = \dot {m} V_{eq} = \dot {m} \left [V_e + \frac {(p_e - P_0)A_c}{\dot {m}} \right ]</math> | :<math>F = \dot {m} V_{eq} = \dot {m} \left [V_e + \frac {(p_e - P_0)A_c}{\dot {m}} \right ]</math> | ||
The total impulse of a rocket is defined as the average thrust multiplied by the total time of propellant burning: | |||
:<math>I = F \Delta T = \int {F dt} = \int {\dot {m} V_{eq}\, dt} = \dot {m} V_{eq}</math> | |||
{{reflist}} | {{reflist}} | ||
Revision as of 16:22, 24 March 2010
Rocket thrust and specific impulse
Thrust is the force (F) which moves a rocket through the air. Thrust is generated by the rocket engine through the reaction of accelerating a mass of gas. The gas is accelerated to the the rear and the rocket is accelerated in the opposite direction. Force may be mathematically expressed as:[1][2]
and also this form, by defining a new term veq :
![{\displaystyle F={\dot {m}}V_{eq}={\dot {m}}\left[V_{e}+{\frac {(p_{e}-P_{0})A_{c}}{\dot {m}}}\right]}](https://wikimedia.org/api/rest_v1/media/math/render/svg/553a0d3d839fca9262578e8eb92a51707a59a33f)
The total impulse of a rocket is defined as the average thrust multiplied by the total time of propellant burning:
- ↑ Rocket Thrust Summary from a website page of the National Aeronautics and Space Administration (NASA)
- ↑ Specific Impulse from a website page of the National Aeronautics and Space Administration (NASA)