Need help finding required Propellant Fraction for equation

AI Thread Summary
To find the required propellant fraction for a cryogenic chemical propulsion system with a specific impulse (Isp) of 450 s and a ΔV of 9.6 km/s, the relevant rocket equation is mprop/mi = 1 - exp(-ΔV/Vex), where Vex is calculated as g0 Isp. Users expressed confusion about how to rearrange the rocket equation to solve for propellant fraction and how to input the exponential function on calculators. The discussion highlighted the importance of understanding the relationship between Isp and exhaust velocity in the context of propulsion calculations. Participants provided guidance on using scientific calculators to compute the necessary values. The conversation emphasized the need for clarity in applying the rocket equation to solve the problem effectively.
BilboBombadillo
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Homework Statement


Consider a cryogenic chemical propulsion system with Isp (specific impulse) = 450 s
Enter the required propellant fraction as a proportion with at least two decimal places.

The ΔVelocity is provided. ΔV = 9.6 km/s

Homework Equations


Rocket equation:
ΔV = Vex x Ln (initial mass/final mass)

The Attempt at a Solution


I'm atrocious at math, yet this question has come may way nonetheless. Do I just reverse the standard rocket equation one uses to find the Delta Velocity?
Propellant/final mass = ΔV x Isp?
I need smart folk.
 
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BilboBombadillo said:

Homework Statement


Consider a cryogenic chemical propulsion system with Isp (specific impulse) = 450 s
Enter the required propellant fraction as a proportion with at least two decimal places.

The ΔVelocity is provided. ΔV = 9.6 km/s

Homework Equations


Rocket equation:
ΔV = Vex x Ln (initial mass/final mass)

The Attempt at a Solution


I'm atrocious at math, yet this question has come may way nonetheless. Do I just reverse the standard rocket equation one uses to find the Delta Velocity?
Propellant/final mass = ΔV x Isp?
I need smart folk.
In the rocket equation you listed, where does Isp fit in? Is there another relevant equation, or perhaps one that is more relevant to your problem?
 
Apologies I forgot the actual equation. The rocket equation I figured was necessary anyway, as no mass information is provided.
Here:
Propellant Fraction:
mprop/mi = 1 - exp(-ΔV/Vex)
 
Isp is part of the Exhaust velocity equation
Vex = g0 Isp
In fact, I think a better question would be - How does one input exp(-ΔV/Vex) on a calculator?
 
BilboBombadillo said:
Isp is part of the Exhaust velocity equation
Vex = g0 Isp
In fact, I think a better question would be - How does one input exp(-ΔV/Vex) on a calculator?
It depends on the kind of calculator you have. If it's a standard scientific calculator, enter ΔV, divide by V, change the sign (usually marked +/-), and then hit the ex button. Some of the fancier calculators these days allow you to enter the formula in the display.
 
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