Homeworks for aerospace dynamics courses with matlab solutions

Applied-Orbital-master
Applied-Orbital-master\.DS_Store
Applied-Orbital-master\HW10
Applied-Orbital-master\HW10\.DS_Store
Applied-Orbital-master\HW10\HW10Script.m
Applied-Orbital-master\HW10\HW10Script.m~
Applied-Orbital-master\HW10\L4.jpg
Applied-Orbital-master\HW10\Transfer.jpg
Applied-Orbital-master\HW10\integrateThreeBodyEquation.m
Applied-Orbital-master\HW10\integrateThreeBodyEquation.m~
Applied-Orbital-master\HW11
Applied-Orbital-master\HW11\Homework11Script.m
Applied-Orbital-master\HW11\Homework11Script.m~
Applied-Orbital-master\HW11\RightAscnFrameToECI.m
Applied-Orbital-master\HW11\eph.m
Applied-Orbital-master\HW11\eph.m~
Applied-Orbital-master\HW11\integrateFourBodyEquation.m
Applied-Orbital-master\HW11\integrateFourBodyEquation.m~
Applied-Orbital-master\HW11\integrateTwoBodyEquation.m
Applied-Orbital-master\HW11\integrateTwoBodyEquation.m~
Applied-Orbital-master\HW11\keplerSolver.m
Applied-Orbital-master\HW11\lambertTransfer.m
Applied-Orbital-master\HW11\lambertTransfer.m~
Applied-Orbital-master\HW11\orbitalElementsToStateVectors.m
Applied-Orbital-master\HW12
Applied-Orbital-master\HW12\.DS_Store
Applied-Orbital-master\HW12\Assignment 12.docx
Applied-Orbital-master\HW12\EclipsedSat.m
Applied-Orbital-master\HW12\EclipsedSat.m~
Applied-Orbital-master\HW12\RightAscnFrameToECI.m
Applied-Orbital-master\HW4
Applied-Orbital-master\HW4\EclipsedSat.m
Applied-Orbital-master\HW4\EclipsedSat.m~
Applied-Orbital-master\HW4\Results updated.rtf
Applied-Orbital-master\HW4\Results.docx
Applied-Orbital-master\HW4\RightAscnFrameToECEF.m
Applied-Orbital-master\HW5
Applied-Orbital-master\HW5\ground_track.asv
Applied-Orbital-master\HW5\ground_track.m
Applied-Orbital-master\HW5\kepler_E.m
Applied-Orbital-master\HW5\ra_and_dec_from_r.m
Applied-Orbital-master\HW5\sv_from_coe.m
Applied-Orbital-master\HW6
Applied-Orbital-master\HW6\Homework 6.docx
Applied-Orbital-master\HW6\Homework6Script.m
Applied-Orbital-master\HW6\Homework6Script.m~
Applied-Orbital-master\HW6\RightAscnFrameToECEF.m
Applied-Orbital-master\HW6\RightAscnFrameToECEF.m~
Applied-Orbital-master\HW6\keplerSolver.m
Applied-Orbital-master\HW6\keplerSolver.m~
Applied-Orbital-master\HW6\orbitalElementsToStateVectors.m
Applied-Orbital-master\HW6\relativePositionVectorsToRTN.m
Applied-Orbital-master\HW7
Applied-Orbital-master\HW7\.DS_Store
Applied-Orbital-master\HW7\ECIToECEF.m
Applied-Orbital-master\HW7\GroundTrack.tif
Applied-Orbital-master\HW7\Homework 7.docx
Applied-Orbital-master\HW7\Homework7Script.m
Applied-Orbital-master\HW7\Homework7Script.m~
Applied-Orbital-master\HW7\RAandDecOverTime.tif
Applied-Orbital-master\HW7\RightAscnFrameToECEF.m
Applied-Orbital-master\HW7\RvsTime.tif
Applied-Orbital-master\HW7\integrateTwoBodyEquation.m
Applied-Orbital-master\HW7\integrateTwoBodyEquation.m~
Applied-Orbital-master\HW7\keplerSolver.m
Applied-Orbital-master\HW7\positionVecToRAandDec.m
Applied-Orbital-master\HW7\semimajorAxisForRepeatingGroundtrack.m
Applied-Orbital-master\HW8
Applied-Orbital-master\HW8\HW8.m
Applied-Orbital-master\HW8\Homework8Script.m
Applied-Orbital-master\HW8\Homework8Script.m~
Applied-Orbital-master\HW8\RightAscnFrameToECEF.m
Applied-Orbital-master\HW8\convertUTCAndDOYToSiderealTimeInDegreesAtGreenwich.m
Applied-Orbital-master\HW8\elevationAndAzimuthToRAandDec.m
Applied-Orbital-master\HW8\elevationAndAzimuthToRAandDec.m~
Applied-Orbital-master\HW8\keplerSolver.m
Applied-Orbital-master\HW8\stateVectorToPerifocalFrame.m
Applied-Orbital-master\HW9
Applied-Orbital-master\HW9\Problem3.asv
Applied-Orbital-master\HW9\Problem3.m
Applied-Orbital-master\HW9\Problem3b.asv
Applied-Orbital-master\HW9\Problem3b.m
Applied-Orbital-master\HW9\fDot_and_gDot.m
Applied-Orbital-master\HW9\f_and_g.m
Applied-Orbital-master\HW9\kepler_U.m
Applied-Orbital-master\HW9\rkf45.m
Applied-Orbital-master\HW9\rv_from_r0v0.m
Applied-Orbital-master\HW9\stumpC.m
Applied-Orbital-master\HW9\stumpS.m
Applied-Orbital-master\HW9\sv_from_coe.m
Applied-Orbital-master\Orbital-Mechanics
Applied-Orbital-master\README.md

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