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| The destination orbit has a radius of $ r_d $ and a velocity of $ v_d = \sqrt{ \mu / r_d } $ were $ \mu = $ 398600.4418 km^3^ / s^2^ . | The destination orbit has a radius of $ r_d $ and a velocity of $ v_d = \sqrt{ \mu / r_d } $ were $ \mu = $ 398600.4418 km^3^ / s^2^. ---- The loop calculation is fairly simple - an 80 kilometer breech altitude launch loop defines a transfer orbit with a perigee $ r_p $ = 6378 + 80 km = 6458 km . The semimajor axis is $ a = 0.5 * ( r_p + r_d ) $, the eccentricity $ e = ( r_d - r_p ) / ( r_d + r_p ) $, the characteristic velocity is $ v_0 = \sqrt{ \mu / ( a * ( 1 - e^2 ) ) } $ , and the apogee velocity is $ v_a = ( 1 - e ) v_0 $. Combining and simplifying: $ {v_a}^2 = ( 1 - e )^2 {v_0}^2 = ( \mu / a ) ( 1 - e )^2 / ( 1 - e^2 ) $ $ {v_a}^2 = ( 2 \mu r_p ) / ( r_d ( r_d + r_p ) ) $ $ v_a = \sqrt{ ( 2 \mu r_p ) / ( r_d ( r_d + r_p ) ) } $ $ \Delta V = v_d - v_a $ |
Orbit Circularization
What is the ΔV needed for apogee insertion into a circular equatorial orbit from a launch loop transfer orbit, and for perigee insertion from a space elevator transfer orbit?
The destination orbit has a radius of 
rd
The loop calculation is fairly simple - an 80 kilometer breech altitude launch loop defines a transfer orbit with a perigee r_p = 6378 + 80 km = 6458 km . The semimajor axis is a = 0.5 * ( r_p + r_d ) , the eccentricity e = ( r_d - r_p ) / ( r_d + r_p ) , the characteristic velocity is v_0 = \sqrt{ \mu / ( a * ( 1 - e^2 ) ) } , and the apogee velocity is v_a = ( 1 - e ) v_0 . Combining and simplifying:
{v_a}^2 = ( 1 - e )^2 {v_0}^2 = ( \mu / a ) ( 1 - e )^2 / ( 1 - e^2 )
{v_a}^2 = ( 2 \mu r_p ) / ( r_d ( r_d + r_p ) )
v_a = \sqrt{ ( 2 \mu r_p ) / ( r_d ( r_d + r_p ) ) }
\Delta V = v_d - v_a