An earlier analysis of lifting satellite entry for circular orbit velocities is extended to the case of parabolic orbit velocities. Simple formulas are derived which yield approximations to the minimum loadings for steep entries. The general advantage of operation on the high-drag side of maximum lift-drag ratio is demonstrated analytically. The optimum character of modulation from maximum lift coefficient is shown.nA principal parameter is shown to be the ratio of maximum lift coefficient to minimum drag coefficient. The analytical results are compared with those of detailed numerical integrations for an entry vehicle with a simplified but realistic lift polar.
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