Maneuvering Spacecraft Orbit Determination Using Polynomial Representation

This paper proposed a polynomial representation-based method for orbit determination (OD) of spacecraft with the unknown maneuver. Different from conventional maneuvering OD approaches that rely on specific dynamic equation, needs no priori information model. The polynomials are used to represent A transformation is made improve convergence and robustness. Extended Kalman Filter (EKF) process incoming observation data by compensating maneuver using polynomials. successfully applicated into problem trigonometric Numerical simulations show eighth-order accurate enough Moreover, Monte Carlo position errors smaller than 1 km, estimated more 0.1 mm/s2 efficient, has potential applications tracking space target.