|Feb28-10, 02:18 AM||#1|
Minimum thrust of engines at lift-off
1. The problem statement, all variables and given/known data
Rocket has a total mass of 3.4 x 10^6 kg at lift-off. The first stage contains 2.0 x 10^6 kg of propellants which is consumed at a rate of 1.4 x 10^4 kg s
Find the minimum thrust of the engines at lift-off?
I would have thought that you needed one more variable to be able to solve this?
2. Relevant equations
3. The attempt at a solution
I used the mass flow x escape velocity and ended up with 15.7 x 10^6 N. It takes 142 sec for the first stage to finish its burn.
I just dont think that this is right - as the next part states that if this thrust is sustained - find the time over which the first stage operates and the acceleration of the vehicle at that time. (Neglect air friction - and suume whole flight is vertical.
Help needed please. Cheers
|Mar1-10, 06:43 PM||#2|
|Sep15-10, 12:29 PM||#3|
Wouldn't the minimum thrust just be m*g? In order to get the rocket moving, you would need at least 3.3*10^7 N of force.
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