Space Propulsion - IAP/TU Wien
Space Propulsion - IAP/TU Wien
Space Propulsion - IAP/TU Wien
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<strong>Space</strong> <strong>Propulsion</strong><br />
Velocity increase in transfer orbit insertion:<br />
ΔV i<br />
= 10.22<br />
− 7.78 = 2.44 [ km / s]<br />
μ<br />
Apogee velocity in transfer ellipse is 2 2*398600 398600<br />
Va = − =<br />
− = 1.60 [ km / s]<br />
r a 42219 24403<br />
a<br />
μ<br />
Velocity increase at circularization:<br />
ΔV circ<br />
= 3.07<br />
−1.60<br />
= 1.47 [ km / s]<br />
Adding up to a total velocity increase of<br />
ΔV tot<br />
= 2.44<br />
+ 1.47 = 3.91 [ km / s]<br />
Fuel consumption is:<br />
⎡ ⎛ V ⎞ ⎤ ⎧ ⎡(3910)<br />
⎤ ⎫<br />
m<br />
p<br />
m<br />
f ⎢exp⎜<br />
Δ<br />
=<br />
⎟ −1⎥<br />
= 1000⎨exp<br />
−1⎬<br />
= 2530<br />
I<br />
⎢<br />
sp<br />
⎩ (3100)<br />
⎥<br />
⎢<br />
⎣ ⎝ ⎠ ⎥⎦<br />
⎣ ⎦ ⎭<br />
[ kg]<br />
The efficiency of the Hohmann transfer comes from the fact that the two<br />
velocity changes are made at points of tangency between the trajectories.