CDA Aа=-2л- p(rperi)a² m Accodingly for nearly-circular orbits, expressions for the change of the orbital CDA a² ΔΡ = -6л²² p(rperi) m СРА Av' =π- -P(rperi)av m A rought approximation for the lifetime of a satellite is: H L≈ Δα Ae=0

CDA Aа=-2л- p(rperi)a² m Accodingly for nearly-circular orbits, expressions for the change of the orbital CDA a² ΔΡ = -6л²² p(rperi) m СРА Av' =π- -P(rperi)av m A rought approximation for the lifetime of a satellite is: H L≈ Δα Ae=0

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 9.40P

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Question

You are interested in how long it takes for the ISS to naturally deorbit. Compute in the analytic approximation of the change in orbital elements per revolution and compare to the single-step approximation formula for the lifetime.

I have attached an image of a formula for the change in semi-major axis per revolution and the formula to calculate the lifetime of a satellite. I want to know what H is and its value? Also, how do you compare the two because one is the change in semi-major axis and the other is lifetime?

CDA
Aа=-2л- p(rperi)a²
m
Accodingly for nearly-circular orbits, expressions for the change of the orbital
CDA
a²
ΔΡ = -6л²² p(rperi)
m
СРА
Av' =π- -P(rperi)av
m
A rought approximation for the lifetime of a satellite is:
H
L≈
Δα
Ae=0

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