Questions tagged [rocket-equation]
Equation stating that the change in velocity (delta-v) of a single stage rocket is equal to the exhaust velocity times the natural log of the ratio of final to initial mass, named after Russian scientist Konstantin Tsiolkovsky.
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Would that asteroid transport be possible?
I did the mistake of watching an episode of the Science Fiction series "For All Mankind". There they are trying to catch an asteroid in order to bring it back to Mars. I know this series is ...
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How can I calculate the altitude my waterrocket will fly with a certain amount of pressure?
I am trying to calculate how high my waterrocket will fly before launching it at different pressure using the Tsiolkovsky rocket equation. However, I stumbled upon an issue since the altitude that it ...
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Engine most likely to be available in the next 80 years to accelerate a craft at 1G for 4 weeks [closed]
I am wondering what type of engine would most likely be available in the next 80 that can constantly accelerate a spacecraft at 1G. Preferably, it could accelerate it for 4 weeks.
The engine could be ...
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What should be the fuel mass of a hypersonic (Mach 7) rocket using APCP fuel that would deliver a 50 gram payload?
Well, I used this rocket calculator besides asking ChatGPT and BingGPT and both gave me similar answers where the amount of fuel would be around 300 to 4000 grams of APCP fuel. And 30 to 100 grams for ...
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How high will this rocket be, when MECO occurs?
Find the altitude of the rocket at the time of engine cut-off.
Rocket Mass = 369208 kg,
Rocket Area = 391 m2,
Fuel = 170697 L,
Fuel density = 21 kg/l,
Exhaust Speed = 1338 m/s,
Exhaust Area = 164 m2
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What was the exhaust pressure of the Saturn V? [duplicate]
I am trying to write some code to simulate rocket launches, and I am doing a proof of concept using the Apollo 11 as a model, to fill my values. When calculating thrust I am using the equation:
F=m⋅Ve+...
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How do you find the propellant mass needed to reach an specified altitude? (altitude at end of burn plus altitude during coast)
This question is basically entirely explained in the title, but I'll explain it more so this question doesn't get shut down. Basically, does anyone have an equation to find the propellant mass(solid) ...
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What is missing in the conversion of specific impulse from units of seconds to thrust/mass flow rate? [duplicate]
I was trying to get the Specific Impulse of the Saturn V engines, hoping for a value in N/kg/s, as I need to know the mass consumption rate per thrust value. Any and all sources give me the value in ...
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How to calculate the optimal mass ratio for a multistage water rocket?
I do know about the Tsiolkovsky rocket equation for optimising multistage rockets, however the equation requires a fixed exhaust velocity which is something that water rockets don't have, however I ...
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How to estimate the fuel required to send 1 kg to lower mars orbit?
Imagine a rocket with a payload of 1 kg. How much liquid fuel would be required to send that 1 kg payload to lower mars orbit. (1 kg is just the payload not the whole dry mass of the rocket) I want ...
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How is the rocket equation affected by changing the number of engines or boosters? [duplicate]
Specific impulse is not affected by the number of boosters or engines on a rocket, correct? Let's say I take a rocket with two SRBs and add to more for the first stage. The specific impulse of the ...
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How to account for burned fuel mass when calculating spacecraft acceleration?
I thought I could simply remove half of the burned fuel mass to account for the mass lost during the engine burn.
But I could not find a Newton's Second Law formula Calculator that would allow that, ...
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Rocket maximum distance [closed]
let's say I have a liquid rocket
what would maximize the distance traveled by the rocket thus consume less fuel
constant velocity or acceleration or why?
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Comparing Newtons 2nd law and Tsiolkovskys
I've been attempting to simulate a rocket launch, using:
ΣF= ma + md/dt*v
If ΣF is simplified to only include F_m, being the rocket's thrust, the equation, if solved for a, is:
a = (F_m - md/dt*v)/...
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rocket propulsion elements [closed]
i tried to solve the following problem
this rocket engine area is cut off at 50% of the exit area, calculate the new Mach value.
data old engine:
P1=2068Mpa , chamber temp 2222k , flow mass 1kg/sec ,...
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