Space Flight Dynamics by Craig A. Kluever

Author:Craig A. Kluever
Language: eng
Format: epub, pdf
ISBN: 9781119157847
Publisher: John Wiley & Sons, Inc.
Published: 2018-05-07T00:00:00+00:00

7.12 Determine the two velocity increments, Δv1 and Δv2, for the coplanar geocentric orbit transfer shown in Figure P7.12. The initial and final orbit radii are r1 = 6,878 km and r2 = 34,000 km, respectively. The first impulse is tangent to the initial circular orbit and it establishes a transfer ellipse with an apogee altitude of 35,000 km. Figure P7.12

Problems 7.13 and 7.14 involve the two geocentric coplanar orbits shown in Figure P7.13. Both orbits share a common apse line

7.13 Determine the two‐impulse orbit transfer from the initial orbit to the final orbit with the minimum total Δv. Compute the total Δv and the perigee and apogee of the orbit transfer between the initial and final orbits shown in Figure P7.13. Figure P7.13

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