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| Main Authors: | , , , |
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| Format: | Preprint |
| Published: |
2025
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| Subjects: | |
| Online Access: | https://arxiv.org/abs/2503.23628 |
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Table of Contents:
- This paper employs an alternate dynamical model of the circular restricted three body problem to quantify uncertainties associated with spacecraft thrusting maneuvers. A non-product quadrature scheme known as Conjugate Unscented Transform (CUT) is employed to determine the higher order system sensitivities through a computationally efficient data driven approach. Moreover, the CUT scheme, in conjunction with a sparse approximation method, is used to find an analytical representation of the time evolution of the state probability density function (pdf).