Accession Number:

AD0600458

Title:

ERROR DERIVATIVES FOR ELLIPTIC ORBITS.

Descriptive Note:

Corporate Author:

AEROSPACE CORP EL SEGUNDO CALIF

Personal Author(s):

Report Date:

1964-02-26

Pagination or Media Count:

31.0

Abstract:

When an increment of velocity is applied to an orbiting vehicle in an attempt to bring it to earth, errors will exist in the assumed position and velocity of the vehicle and in the applied velocity increment. If these errors are sufficiently small, a linear error analysis will suffice for determining their effects on quantities of interest at later times such as impact point coordinates. Formulas are derived in this report for the partial derivatives required for such an error analysis, assuming a non-rotating, spherical earth with no atmosphere. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE