A theory has been developed which determines the influence of
primary errors upon the dispersion of the apogee and perigee altitudes
of the orbit of a satellite vehicle. It is seen that the apogee and
perigee altitudes are influenced chiefly by the errors in velocity
and flight-path angle at burnout of the next-to-last stage, guidance,
velocity increment and thrust alinement, and pitching rate at ignition
of the last stage. The theory will allow the probability of a satellite
vehicle successfully obtaining a given orbit to be determined. A series
of charts which greatly reduce the amount of work required in applying
the theory are included.
The theory has been applied to the Scout missile for a range of
injection altitudes and one payload weight which is representative of
the capability of this vehicle. One of the major requirements of any
future satellite vehicle will be an improved guidance system so that the
Scout probably will be the worst case to which the theory will be applied.
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