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

College Physics

11th Edition

ISBN:9781305952300

Author:Raymond A. Serway, Chris Vuille

Publisher:Raymond A. Serway, Chris Vuille

Chapter1: Units, Trigonometry. And Vectors

Section: Chapter Questions

Problem 1CQ: Estimate the order of magnitude of the length, in meters, of each of the following; (a) a mouse, (b)...

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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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