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Space Propulsion - IAP/TU Wien

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<strong>Space</strong> <strong>Propulsion</strong><br />

Check<br />

for tankage factor φ 0, we have rockets consisting of payload<br />

and fuel only and single- and „multistage“ rockets with same<br />

payload and fuel masses must have the same ΔV<br />

R −1<br />

ρ = → R −1<br />

1−<br />

φ<br />

( R −1)<br />

( 1+<br />

φ ) ρ → −1<br />

ψ = R<br />

ΔV<br />

sin gle<br />

=<br />

I<br />

sp<br />

⎡ 1+<br />

φ<br />

.ln⎢<br />

⎣φ<br />

+<br />

( 1+<br />

ψ )<br />

⎤<br />

⎡ 1<br />

⎢<br />

⎣ R<br />

n ⎥ → I<br />

sp<br />

ln = nI<br />

n sp<br />

ln( R)<br />

− −<br />

⎦<br />

⎤<br />

⎥<br />

⎦<br />

=<br />

ΔV<br />

multi

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