Orbit n3 in Ω n2

International Edition---engineering Mechanics: Statics, 4th Edition
4th Edition
ISBN:9781305501607
Author:Andrew Pytel And Jaan Kiusalaas
Publisher:Andrew Pytel And Jaan Kiusalaas
Chapter9: Moments And Products Of Inertia Of Areas
Section: Chapter Questions
Problem 9.46P
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 Let Hill frame H = {i-hat_r, i-hat_θ, i-hat_h} be the orbit frame of the LMO satellite. These base vectors are generally defined as:
i-hat_r = r_LM / |r_LM|, i-hat_theta = i-hat_h X i-hat_r, i-hat_h = r_LM X r-dot_LMO /( | r_LM X r-dot_LMO | )
 How would you:
 • Determine an analytic expressions for [HN]

Orbit
n3
in
Ω
n2
Transcribed Image Text:Orbit n3 in Ω n2
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