Reachability-Based Approach for Search and Detection of Maneuvering Cislunar Objects

Hall, Zach W.; Schwab, David J.; Eapen, Roshan Thomas; Singla, Puneet

doi:10.2514/6.2022-0853

Cited by 4 publications

(1 citation statement)

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“…Hall and Singla developed a unified reachability-based framework for tracking lost-in-space noncooperative maneuvering targets [33,34]. Their method uses numerical quadrature methods to efficiently propagate the reachability sets of the maneuvering target [35,36], which can be further employed for searching lost-in-space targets and tasking sensors, maneuver detection and estimation, and orbit estimation [37].…”

Section: Introductionmentioning

confidence: 99%

Orbit Determination for Impulsively Maneuvering Spacecraft Using Modified State Transition Tensor

Zhou,

Qiao,

Macdonald

2024

Journal of Guidance, Control, and Dynamics

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This paper proposes a method to accurately resolve orbit determination for a spacecraft with unknown impulsive maneuvers. The proposed method handles the unknown impulsive maneuver by incorporating the magnitude, direction, and time of the impulsive maneuver into the estimation parameter vector. First, a modified state transition tensor (STT) is proposed via orbit division and segment connection, allowing the orbit to be directly propagated under the effects of impulsive maneuver uncertainties. Then, based on the modified STT, a second-order measurement model is established with the estimation parameter vector as the input. Combining the second-order measurement model with observations, a second-order optimal solution is derived to correct the estimation parameters. The spacecraft orbit, together with the magnitude, direction, and time of the impulsive maneuver, are simultaneously estimated in an iterative framework. The performance of the proposed method is validated in a low-Earth-orbit case and a high-Earth-orbit case. Simulations show that the proposed method outperforms its linear version in terms of convergence, accuracy, and uncertainty quantification capacity. Its maneuver reconstruction and orbit estimation errors are one order of magnitude less than those of competitive methods. Moreover, the proposed method can handle severe conditions and is robust to initial guesses.

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