Determine an interplanetary Earth-Jupiter mission that uses a heliocentric Hoh- mann transfer. Assume coplanar concentric planetary...

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Determine an interplanetary Earth-Jupiter mission that uses a heliocentric Hoh- mann transfer. Assume coplanar concentric planetary orbits using the data in Table 10.3. Determine the following parameters: a) Hyperbolic departure velocity, v in km/s b) Hyperbolic arrival velocity, v in km/s c) Hohmann-transfer flight time in days d) Phase angle at departure e) Departure date for first launch opportunity after January 1, 2020. Table 10.3 Planetary ephemeris for the epoch January 1, 2000. Planet Semimajor axis, a (AU) Mercury 0.38710 Venus Earth Eccentricity, e 0.20563 0.72333 0.00677 1.00000 0.01671 1.52368 0.09340 5.20260 0.04849 9.55491 0.05551 Mars. Jupiter Saturn Uranus 19.21845 0.04630 Neptune 30.11039 0.00899 Source: Adapted from Ref. [3]. Inclination, i (°) 7.005 3.394 0.000 1.850 1.303 2.489 0.773 1.770 Longitude of the ascending node, Ω (°) 48.331 76.680 Undefined 49.558 100.464 113.666 74.006 131.784 Longitude of perihelion, w (°) 77.456 131.564 102.937 336.060 14.331 93.057 173.005 48.124 True longitude at epoch, lo (°) 252.251 181.980 100.466 355.433 34.351 50.077 314.055 304.349 Determine an interplanetary Earth-Jupiter mission that uses a heliocentric Hoh- mann transfer. Assume coplanar concentric planetary orbits using the data in Table 10.3. Determine the following parameters: a) Hyperbolic departure velocity, v in km/s b) Hyperbolic arrival velocity, v in km/s c) Hohmann-transfer flight time in days d) Phase angle at departure e) Departure date for first launch opportunity after January 1, 2020. Table 10.3 Planetary ephemeris for the epoch January 1, 2000. Planet Semimajor axis, a (AU) Mercury 0.38710 Venus Earth Eccentricity, e 0.20563 0.72333 0.00677 1.00000 0.01671 1.52368 0.09340 5.20260 0.04849 9.55491 0.05551 Mars. Jupiter Saturn Uranus 19.21845 0.04630 Neptune 30.11039 0.00899 Source: Adapted from Ref. [3]. Inclination, i (°) 7.005 3.394 0.000 1.850 1.303 2.489 0.773 1.770 Longitude of the ascending node, Ω (°) 48.331 76.680 Undefined 49.558 100.464 113.666 74.006 131.784 Longitude of perihelion, w (°) 77.456 131.564 102.937 336.060 14.331 93.057 173.005 48.124 True longitude at epoch, lo (°) 252.251 181.980 100.466 355.433 34.351 50.077 314.055 304.349

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a Hyperbolic departure velocity v in kms The hyperbolic departure velocity v is the velocity of the spacecraft at the point of departure from Earth This velocity is calculated using the equation v 2r1 ... View the full answer