Initial Identification of Thrust and Orbit Elements for Continuous Thrust Spacecraft in Circular Orbit

Abstract

Continuous thrust spacecraft in circular orbits have had a great influence on the identification and cataloging of space targets. Gaussian-type orbital element variational equations are simplified and approximated. Ground-based radar observation datasets are transformed into orbit elements datasets. The initial thrust and orbit elements are obtained by optimally solving the spatial parameter error sum of squares minimization problem with the Levenberg–Marquardt method. The simulation analysis is carried out under the high-precision orbit model, and the solution error of tangential acceleration is around 5 × 10−7 m/s2, and that of normal acceleration is around 3 × 10−6 m/s2; the accuracy of the semi-major axis is 350 m, and the accuracy of inclination is 0.095°. The method is applicable to the preliminary identification of thrust and orbit elements for circular orbit continuous thrust spacecraft and can provide reliable initial values for the subsequent precision orbit determination of such spacecraft.

Deployment of Constellation with Different Inclinations Using the Nodal Precession and Thrust

“…To maximize the change in inclination or RAAN, the normal thrust needs to change direction at a phase-symmetric position ( ϑ = ±π/2 or ϑ = 0, π). For near-circular orbits, Bruce [ 25 ] and Zhao [ 26 ] gives equations for the control of the continuous thrust that changes direction at ϑ = ±π/2 and ϑ = 0, π.…”

“…According to the characteristics of continuous thrust dynamics [ 26 ], the total velocity increment required from a 0 to a f is . where a 0 is the semi-major axis of the parking orbit and a f is the semi-major axis of the target orbit.…”

“…According to the characteristics of continuous thrust dynamics [26], the total velocity increment required from a 0 to a f is ∆V a const .…”