2. An earth-orbiting spacecraft is known to have the following orbital elements: a = 15000 km e = 0.3 i = 55 deg v = 35 deg Ω = 130 deg w = 260 deg Find the position and velocity vectors (expressed in ECI coordinates). 3. Complete the LEO-to-GEO 'Hohmann Transfer with Split Plane Change' problem defined in class. Specifically, define the optimal amounts of inclination that should be removed at perigee and apogee and the minimum AVT. Assume an initial circular orbit with altitude 300 km and inclination 28.5 deg.

2. An earth-orbiting spacecraft is known to have the following orbital elements: a = 15000 km e = 0.3 i = 55 deg v = 35 deg Ω = 130 deg w = 260 deg Find the position and velocity vectors (expressed in ECI coordinates). 3. Complete the LEO-to-GEO 'Hohmann Transfer with Split Plane Change' problem defined in class. Specifically, define the optimal amounts of inclination that should be removed at perigee and apogee and the minimum AVT. Assume an initial circular orbit with altitude 300 km and inclination 28.5 deg.

Name: 2. An earth-orbiting spacecraft is known to have the following orbita
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Description: 2. An earth-orbiting spacecraft is known to have the following orbital elements:a 15000 km55 dege = 0.3@== 130 deg260 deg35 degFind the position and velocity vectors (expressed in ECI coordinates).=V =3. Complete the LEO-to-GEO 'Hohmann Transfer wit

Physics for Scientists and Engineers: Foundations and Connections

1st Edition

ISBN:9781133939146

Author:Katz, Debora M.

Publisher:Katz, Debora M.

Chapter7: Gravity

Section: Chapter Questions

Problem 15PQ: When Sedna was discovered in 2003, it was the most distant object known to orbit the Sun. Currently,...

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2. An earth-orbiting spacecraft is known to have the following orbital elements:
a 15000 km
55 deg
e = 0.3
@=
= 130 deg
260 deg
35 deg
Find the position and velocity vectors (expressed in ECI coordinates).
=
V =
3. Complete the LEO-to-GEO 'Hohmann Transfer with Split Plane Change problem
defined in class. Specifically, define the optimal amounts of inclination that should be
removed at perigee and apogee and the minimum AVT. Assume an initial circular orbit
with altitude 300 km and inclination 28.5 deg.

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