Twoimpulse orbit transfer error analysis via covariance matrix
Abstract
An algorithm for the determination of the orbit insertion errors in a twoimpulse, noncoplanar orbital transfer, with fixed time between the impulses, is presented. Inputs to the algorithm are the covariance matrices of the source errors (initial conditions, errors with the first and second stage) and the nominal parameters of the transfer. The results yield the covariance matrix of the postorbit insertion errors (position and velocity), also expressed in terms of the final orbit element errors (semimajor axis, eccentricity, inclination, right ascension of the ascending node). Although geared to the analysis of Shuttlebased transfer missions, some of which are characterized by large plane changes, the algorithm has the flexibility for different applications.
 Publication:

AIAA, Aerospace Sciences Meeting
 Pub Date:
 January 1979
 Bibcode:
 1979aiaa.meetU....P
 Keywords:

 Covariance;
 Error Analysis;
 Matrices (Mathematics);
 Orbit Calculation;
 Transfer Orbits;
 Algorithms;
 Multistage Rocket Vehicles;
 Orbital Elements;
 Space Shuttles;
 Astrodynamics