ERROR DERIVATIVES FOR ELLIPTIC ORBITS.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 26, 1964
- Accession Number
- AD0600458
Entities
People
- E. R. Lancaster
Organizations
- The Aerospace Corporation