A computer program was developed which performs an error analysis of a minimum-fuel, finite-thrust, transfer maneuver between two Keplerian orbits in the vicinity of Mars. The method of analysis is the Monte Carlo approach where each off-nominal initial orbit is targeted to the desired final orbit. The errors in the initial orbit are described by two covariance matrices of state deviations and tracking errors. The function of the program is to relate these errors to the resulting errors in the final orbit. The equations of motion for the transfer trajectory are those of a spacecraft maneuvering with constant thrust and mass-flow rate in the neighborhood of a single body. The thrust vector is allowed to rotate in a plane with a constant pitch rate. The transfer trajectory is characterized by six control para meters and the final orbit is defined, or partially defined, by the desired target parameters. The program is applicable to the deboost maneuver (hyper bola to ellipse), orbital trim maneuver (ellipse to ellipse), fly-by maneuver orbitsmars (planet) (hyperbola to hyperbola), escape maneuvers (ellipse to hyperbola), and de orbit maneuver. (Author)
A Monte Carlo Error Analysis Program for Near-MARS, Finite-Burn, Orbital Transfer Maneuvers
1972
70 pages
Report
Keine Angabe
Englisch