Abstract
State uncertainties in a spacecraft’s relative motion lead to trajectory deviation. The volume that enclosing all the potential relative position due to initial state uncertainty can be geometrically described as the relative reachable domain (RRD). A general method is developed to determine the envelope of RRD in 3D space for arbitrary reference orbits. At any given time, the plane perpendicular to the instant nominal trajectory is defined as the reference plane. On each reference plane, the envelope of RRD is generated by a revolution of maximum position error vectors. Thus, the problem is transformed to a problem of solving a system of nonlinear equations. Comparison between the solved RRD and the results of Monte Carlo runs, which are propagated by nonlinear full dynamical model of relative motion and can be regarded as the true results, is presented as the numerical example to validate the effectiveness of the proposed method.
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Shi, H., Tian, T., Zhao, X., Xiao, Y. (2019). Modified Method for Orbit Relative Reachable Domain with State Uncertainties. In: Sun, F., Liu, H., Hu, D. (eds) Cognitive Systems and Signal Processing. ICCSIP 2018. Communications in Computer and Information Science, vol 1005. Springer, Singapore. https://doi.org/10.1007/978-981-13-7983-3_35
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DOI: https://doi.org/10.1007/978-981-13-7983-3_35
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