## A study of some transition matrix assumptions in circumlunar navigation theory |

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_0T x 0T x 2_OT 2OT x 56 hours 5OT x Aeronautics and Space circumlunar missions CIRCUMLUNAR NAVIGATION THEORY compute future deviations displacement and velocity displacement partial derivatives disturbance or shift ę-OT ę.Oi Earth's oblateness ęOi ęOi x ęOT ęOT x equatorial bulge ft/sec g-OT hours after insertion increasing the disturbance individual effects initial displacement insertion position Jones and Alton linear Mayo midcourse navigation systems missions to compute Moon Moon's mass Moon's sphere NASA TN National Aeronautics nominal partial derivatives nominal trajectory position and velocity position partial derivative reference trajectory reference-trajectory position Ruben significant figures Space Administration statute miles systems for circumlunar TECHNICAL NOTE D-1812 trajec trajectory parameters trajectory were studied transition matrices utilized TRANSITION MATRIX ASSUMP two-body problems utilized in midcourse velocity partial derivative velocity per unit x id+ x OT2 x OT5 x T0 x tO5 xo y0 y0 zo xo