Analytical Framework for Space Debris Collision Avoidance Maneuver Design

An analytical formulation for collision avoidance maneuvers involving a spacecraft and space debris is presented, including solutions the maximum deviation minimum probability cases. Gauss’s planetary equations relative motion are used to map at given time displacements predicted close approach. The model then extended changes in state between two times, allowing one propagate covariance matrices. reduces optimization problem an eigenproblem, both probability. Two cases, total impact parameter, compared large set of spacecraft–debris conjunction geometries derived from European Space Agency’s Meteoroid Debris Terrestrial Environment Reference (MASTER-2009) model. Moreover, parameter assuming covariances known maneuver time, evaluate net effect lead In all analyzed b-plane leverage its natural separation phasing geometry change effects. Both uncertainties grow along axis long limiting reduction