Space Propulsion - IAP/TU Wien

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Space Propulsion Example 3: Hohman transfer from circular Earth orbit (altitude = 200 km) to geostationary orbit (r = 42219 km); what is fuel consumption to bring a 1 t payload to GEO with a specific impulse of 3100 [m/s]? Velocity in LEO: Velocity in LEO: 398,600 V = μ = = r 6387 + 200 7.78 [ km / s] Velocity in GEO similarly is 3.07 [km/s] Semimajor axis of transfer ellipse is ( 6387 + 200) + 42219 a = = 2 24403 [ km] Perigee velocity in transfer ellipse is: V p = 2μ μ − = r a p 2*398600 − 6387 + 200 398600 24403 = = 10.22 [ km / s] Example 3, cont‘d
Space Propulsion Velocity increase in transfer orbit insertion: ΔV i = 10.22 − 7.78 = 2.44 [ km / s] μ Apogee velocity in transfer ellipse is 2 2*398600 398600 Va = − = − = 1.60 [ km / s] r a 42219 24403 a μ Velocity increase at circularization: ΔV circ = 3.07 −1.60 = 1.47 [ km / s] Adding up to a total velocity increase of ΔV tot = 2.44 + 1.47 = 3.91 [ km / s] Fuel consumption is: ⎡ ⎛ V ⎞ ⎤ ⎧ ⎡(3910) ⎤ ⎫ m p m f ⎢exp⎜ Δ = ⎟ −1⎥ = 1000⎨exp −1⎬ = 2530 I ⎢ sp ⎩ (3100) ⎥ ⎢ ⎣ ⎝ ⎠ ⎥⎦ ⎣ ⎦ ⎭ [ kg] The efficiency of the Hohmann transfer comes from the fact that the two velocity changes are made at points of tangency between the trajectories.
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Page 19 and 20: Space Propulsion Elliptical orbits
Page 21 and 22: Space Propulsion Tsiolkovsky equati
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Page 35 and 36: Space Propulsion coplanar orbit cha
Page 37 and 38: Space Propulsion Example 1: Simple
Page 39: Space Propulsion Hohmann transfer:
Page 43 and 44: Space Propulsion Combined maneuver:
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Page 49 and 50: Space Propulsion vectorial velocity
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Page 59 and 60: Space Propulsion Spiraling up time
Page 61 and 62: Space Propulsion Comparison of Hohm
Page 63 and 64: Space Propulsion Attitude maneuvres
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Page 67 and 68: Space Propulsion Attitude control t
Page 69 and 70: Space Propulsion Kinetics for rotat
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Page 73 and 74: Space Propulsion Example 6: One-Axi
Page 75 and 76: Space Propulsion Example 7: Precess
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Page 79 and 80: Space Propulsion Example 8: Limit-C
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