Failure Mitigation during Rendezvous in Cislunar Orbit

Innocenti, Mario; D’Onofrio, Fabio; Bucchioni, Giordana

doi:10.2514/6.2022-0861

Cited by 2 publications

(3 citation statements)

References 18 publications

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“…In addition, the Local Vertical Local Horizon (LVLH) frame is also used, because of its convenience from the guidance, navigation and control point of view. The results presented herein are taken by previous work by the authors and details can be found primarily in Innocenti et al (2022).…”

Section: Relative Motion Dynamicsmentioning

confidence: 99%

“…The relative velocity at each hold point is assumed to be zero, and the initial mean anomaly and time of flight of each segment are selected for full safety of the mission. The reference sequence is defined below in local vertical local horizon components, taken from Innocenti et al (2022):…”

Section: Nominal Rendezvousmentioning

confidence: 99%

“…An exhaustive analysis of performance under failure is beyond the scope of the paper and extensive Montecarlo simulations of hold point reallocation, in order to satisfy passive safety can be found in Bucchioni (2021), Innocenti et al (2022) and De Benedetti et al (2022). Tables 1-3 present a summary of the reallocation and they are reported here courtesy of the authors.…”

Section: Example Of the Synthesis Of A Safe Trajectorymentioning

confidence: 99%

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Dynamics and control analysis during rendezvous in non-Keplerian Earth—Moon orbits

Innocenti

Bucchioni

Franzini³

et al. 2022

Front. Space Technol.

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The paper describes the development of a framework capable of addressing some fundamental issues in the analysis of proximity operations between two spacecraft that are operating within a three-body model defined by two primaries and the spacecraft themselves. The main objective is to enable the capability of analysing dynamic and control issues during an automated rendezvous between a vehicle and a passive space station orbiting around the Earth - Moon L2 Lagrangian point on a near rectilinear halo orbit. The paper presents first a restricted three body model dynamics and a nominal approach trajectory, followed by an analysis of the influence of assumed actuators and sensors. Critical aspects such as selected failures are investigated, in order to ensure passive safety of the mission using impulsive maneuvers. An example of closed loop guidance in the near range is also presented and the overall performance are validated with an Ephemeris model available in the literature.

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Section: Relative Motion Dynamicsmentioning

confidence: 99%

Section: Nominal Rendezvousmentioning

confidence: 99%

Section: Example Of the Synthesis Of A Safe Trajectorymentioning

confidence: 99%

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