Exploiting manifolds of <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML" display="inline" id="d1e1972" altimg="si68.svg"><mml:msub><mml:mrow><mml:mi>L</mml:mi></mml:mrow><mml:mrow><mml:mn>1</mml:mn></mml:mrow></mml:msub></mml:math> halo orbits for end-to-end Earth–Moon low-thrust trajectory design

Singh, Sandeep Kumar; Anderson, B.D.O.; Taheri, Ehsan; Junkins, John L.

doi:10.1016/j.actaastro.2021.03.017

Cited by 20 publications

(3 citation statements)

References 39 publications

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“…The short-term efforts will be focused on sustaining human presence on our nearest neighbor in the cosmos, the Moon [1,2]. A variety of mission architectures have been explored in this context, which typically include sending manned spacecraft to a periodic orbit (an orbit from the Near Rectilinear Halo Orbit (NRHO) family) around the Earth-Moon Lagrange Point (L 2 ) [3,4], then maneuvering the spacecraft to a Low-Lunar Orbit (LLO) [5,6] and finally detaching the lander from the orbiter and eventually descending onto the lunar surface, making a soft landing on the lunar terrain. NASA's Commercial Lunar Payload Services (CLPS) [7,8] is a high-risk, highreward approach for performing key science missions and technology demonstration that would be instrumental in enabling a sustained human presence.…”

Section: Introductionmentioning

confidence: 99%

Probabilistic Regression for Autonomous Terrain Relative Navigation via Multi-Modal Feature Learning

Kim,

Rolen,

Singh

2024

Preprint

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The extension of human spaceflight across an ever-expanding domain, in conjunction with intricate mission architectures demands a paradigm shift in autonomous navigation algorithms, especially for the powered descent phase of planetary landing. Deep learning architectures have previously been explored to perform low-dimensional localization with limited success. Due to the expectations regarding novel algorithms in the context of real missions, the proposed approaches must be rigorously evaluated in extraneous scenarios and demonstrate sufficient robustness. In the current work, a novel formulation is proposed to train CNN-based deep learning (DL) models in a multi-layer cascading architecture and utilize the resulting classification probabilities as regression weights to estimate the two-dimensional position of the lander spacecraft. The approach leverages image intensity as well as embedded depth information to effectively determine the location of a spacecraft relative to the observed terrain. The efficacy of the proposed DL architecture and the subsequent state-estimation framework is demonstrated using several simulated scenarios and shows promise.

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Section: Introductionmentioning

confidence: 99%

Probabilistic Regression for Autonomous Terrain Relative Navigation via Multi-Modal Feature Learning

Kim,

Rolen,

Singh

2024

Preprint

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“…In this model, the lunar orbit is still assumed as a circle, and the barycenter of the Earth+Moon is assumed to be on a circular orbit around the Sun (Simó et al 1995). This model has been extensively used in studies of orbital motions in the Earth-Moon system (Abouelmagd et al 2021;Jorba & Nicolás 2021;Singh et al 2021). The problem with the BCP model is that it is incoherent.…”

Section: Introductionmentioning

confidence: 99%

The Main Problem of Lunar Orbit Revisited

Hou

2023

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A novel algorithm based on the Lindstedt–Poincaré method is proposed to construct an analytical solution of the lunar orbit. Based on the analytical solution, a numerical fitting algorithm is proposed to improve the coefficients of the analytical solution so that its accuracy can reach the level of a few kilometers within 20 yr. By fitting our solution to the long-term JPL ephemerides, we are able to recover the receding speed of the Moon from the Earth due to tidal effects. The proposed algorithm also provides a general way to treat the third-body perturbation in rectangular coordinates.

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“…Bolliger (2019) examined transfers between the Near-Rectilinear Halo Orbit (NRHO), and periodic orbits termed the "butterfly" family. Invariant manifolds of periodic orbits were used to design transfers in cislunar space, such as transfers from a super-Geostationary Transfer Orbit (sGTO) to NRHOs (Singh et al, 2021a;Singh et al, 2021c), and a Lunar Polar Orbit (Singh et al, 2021b). For a far-range rendezvous, and Schulte et al (2020) studied the impulsive maneuver method, and Lizy-Destrez et al ( 2019) studied the manifold splicing method.…”

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confidence: 99%

Phasing analysis on DRO with impulsive maneuver

Wang

Zhang

2023

Front. Astron. Space Sci.

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The cis-lunar periodic orbit exhibits some unique dynamic characteristics. Among them is the distant retrograde orbit, which has long-term stability and is one of the ideal candidate deployment orbits for cis-lunar space stations and deep-space exploration transfer stations. Orbiting, rendezvous, and docking are among the flight operations involved in space station on-orbit construction, material supply, spacecraft monitoring, and other tasks. Suitable initial conditions can be created for these operations by shortening the relative distance between spacecraft through phasing. In this study, the characteristics of a two-impulse phasing orbit on a distant retrograde orbit (DRO) are summarized, and its phasing ability is globally analyzed. Based on these analyses, a phasing optimization problem was presented and solved. Using DRO’s dynamic characteristics, a DRO multi-impulse phasing rolling solution method is presented. For accuracy purposes, the orbit determination error is also considered in this method. The simulation analysis was performed using the circular restricted three-body problem (CR3BP) dynamic model and the ephemeris model. Compared with the results of two-impulse phasing, this method reduces the offset of the end position of the DRO phasing orbit from hundreds to tens of kilometers. This result satisfies the relative distance requirements for subsequent spacecraft operations. The total pulse requirement of this phasing method for the two models was within a reasonable and feasible range.

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Exploiting manifolds of L1 halo orbits for end-to-end Earth–Moon low-thrust trajectory design

Cited by 20 publications

References 39 publications

Probabilistic Regression for Autonomous Terrain Relative Navigation via Multi-Modal Feature Learning

Probabilistic Regression for Autonomous Terrain Relative Navigation via Multi-Modal Feature Learning

The Main Problem of Lunar Orbit Revisited

Phasing analysis on DRO with impulsive maneuver

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