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VALIDATION OF RESULTS
APPENDIX BEQUATIONS OF MOTION
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4,100 statute miles 40 statute miles angle or firing apogee average distance calculations center of earth center of moon circular lunar orbit CONDITIONo FOR LUNAR counterclockwise curves data in figure earth and moon earth departure trajectory eccentric anomaly English units entering the lunar equations of motion exit from lunar ft/sec geocentric Hamer Huar incremental insertion velocity inertial INoERTION CONDITIONo insertion conditions insertion flight-path angle insertion radius inside the sphere lead angle required longitude limits lun.r lunar impact lunar lead angle lunar miss distance lunar missions lunar sphere lunar trajectories lunar unit minimum insertion velocity motion with respect NAoA TR NarA op.ar orbit equations orhinl otedy oTUDY OF INoERTION PARAMETER oTUDY perilune is reached Perilune longitude plot radii range of insertion re,i required for lunar return trajectory ronditiono seleno selenocentric semilatus rectum shown in figure sphere of influence three-body total trip trajectories which impact vehicle is moving vehicle motion