Time-Fixed Glideslope Guidance for Approaching the Proximity of an Asteroid

Wang, Jinlin; Li, Hai; Lin, Zhangjin; Huo, Hong

doi:10.3390/aerospace8050137

Cited by 2 publications

(2 citation statements)

References 9 publications

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“…The actual circular orbit always has a small eccentricity due to various errors and perturbations, so the design method for hovering orbit based on the assumption of an ideal circular orbit always has certain errors. The design method for the mission spacecraft hovering in an elliptical reference orbit has more extensive applications [25][26][27][28][29].…”

Section: Introductionmentioning

confidence: 99%

Application of the Relative Orbit in an On-Orbit Service Mission

Zhang²,

et al. 2023

Electronics

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To achieve an on-orbit service mission, the mission spacecraft must approach the target spacecraft first, which is based on the spacecraft’s relative motion. To enhance the safety and reliability of on-orbit service missions, the relative hovering orbit was proposed and needed to be studied further. A high-precision design method for hovering orbit is presented based on the relative dynamics model of spacecraft in this paper. Firstly, based on the stability analysis of the spacecraft relative dynamics model, a method to determine the initial value of periodic relative motion orbit is explored, and an example is given to verify the validity of the method. Then, through theoretical analysis, the formulae of control acceleration required during the hovering flying mission were put forward for both without considering perturbation and with considering J2 perturbation, and numerical simulations for hovering orbit were made to verify the feasibility of the approaches proposed. Simulation results show that the control acceleration curves are smooth, which indicates that the hovering flying mission is easier to achieve, and the control method based on sliding mode control theory is adopted for hovering control. The relative hovering method proposed can provide references in space on-orbit service missions for practical engineers.

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Section: Introductionmentioning

confidence: 99%

Application of the Relative Orbit in an On-Orbit Service Mission

Zhang²,

et al. 2023

Electronics

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“…Naturally, its significance has spawned several recent studies on the design of approaching phase trajectories toward small celestial bodies. Wang et al [22] and Qiao et al [23] presented guidance strategies that can be utilized for low-thrust missions. Wang et al studied a time-fixed glideslope method for robust rendezvous, while Qiao et al presented a methodology for designing approaching trajectories that can improve optical navigation performance (observability).…”

Section: Introductionmentioning

confidence: 99%

Analysis of Preliminary Impulsive Trajectory Design for Near-Earth Asteroid Missions under Approaching Phase Constraints

Kim,

Park

2023

Aerospace

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This study investigates the preliminary trajectory design for high-thrust missions to near-Earth asteroids (NEAs), considering distance and phase angle constraints during the approaching phase to enable pre-rendezvous optical navigation and the scientific identification of asteroids. A global optimization algorithm called monotonic basin hopping is used to design Δv-optimal impulsive trajectories both with and without constraints. Comparisons reveal that extending the final leg of the unconstrained reference trajectory and incorporating a few deep-space maneuvers in that final leg can yield a constrained trajectory with a Δv increase of only a few percent. The effects of the phase angle and minimum distance constraint on Δv are also examined. The results indicate that in Δv-optimal constrained trajectories, an additional deep-space maneuver enables the redistribution of maneuvers in the last leg to ideally insert the spacecraft into the constraint cone. However, additional small maneuvers may be necessary at times to ensure that the spacecraft remains within the cone. Based on these findings, we present a two-step approach for the preliminary design of constrained trajectories for NEA missions based on global optimization algorithms. This approach serves as a valuable tool for initial mission design and trade-off analyses involving constraints, fuel usage, and transfer durations.

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Time-Fixed Glideslope Guidance for Approaching the Proximity of an Asteroid

Cited by 2 publications

References 9 publications

Application of the Relative Orbit in an On-Orbit Service Mission

Application of the Relative Orbit in an On-Orbit Service Mission

Analysis of Preliminary Impulsive Trajectory Design for Near-Earth Asteroid Missions under Approaching Phase Constraints

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