ASE 366K - HW 6 Solutions

ASE 366K - HW 6 Solutions - Spacecraft Dynamics HW 6...

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Spacecraft Dynamics HW 6 Results Note: There is no x-component in the Geocentric Equatorial Frame
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Units of Output are in DU and DU/TU EDU>> p=1.85; EDU>> e=0.75; EDU>> inc=90; EDU>> omega =90; EDU>> argp=250; EDU>> f=200; EDU>> [rperi,vperi,requa,vequa] = coe2rvperandequa(p,e,inc,omega,argp,f) rperi = -5.8884 -2.1432 0 vperi = 0.2515 -0.1395 0 requa = 0 0 6.2663 vequa = 0 -0.2171 -0.1886 Source Code %Compute r and v in perifocal and geocentric equatorial frames %from a set of orbital elements %Inputs and outputs are in Canonical units and degrees %Caution: %This only works for elliptical orbits that are not circular or equatorial % author : Drew Jones 20 oct 2009 % % revisions % - %Inputs description range / units % p - semilatus rectum DU % e - eccentricity % inc - inclination -90 to 90 deg % omega - longitude of ascending node 0.0 to 360 deg % argp - argument of perigee 0.0 to 360 deg % f - true anomaly 0.0 to 360 deg % Outputs
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% rperi - pqw position vector DU % vperi - pqw velocity vector
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This note was uploaded on 09/18/2011 for the course ASE 366K taught by Professor Lightsey during the Fall '08 term at University of Texas.

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ASE 366K - HW 6 Solutions - Spacecraft Dynamics HW 6...

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