Rendezvous design in a cislunar near rectilinear Halo orbit

Emmanuel, Blazquez,; Beauregard, Laurent; Lizy-Destrez, Stéphanie; Ankersen, Finn; Capolupo, Francesco

doi:10.1017/aer.2019.126

Cited by 11 publications

(3 citation statements)

References 12 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Rendezvous in a multigravity environment is more complex and challenging due to the increased forces involved. Several researchers have explored the concept of cislunar rendezvous, particularly through trajectory planning and optimization [7,[11][12][13][14][15]. The inclusion of attitude dynamics becomes crucial for the final phase of the close proximity operations.…”

Section: Previous Contributionsmentioning

confidence: 99%

Rendezvous in cislunar halo orbits: Hardware-in-the-loop simulation with coupled orbit and attitude dynamics

et al. 2023

View full text Add to dashboard Cite

Section: Previous Contributionsmentioning

confidence: 99%

Rendezvous in cislunar halo orbits: Hardware-in-the-loop simulation with coupled orbit and attitude dynamics

et al. 2023

View full text Add to dashboard Cite

“…On a follow up work, Lizy-Destrez et al [60] presented methods and results related to strategies for far and close rendezvous, and compared different linear and nonlinear models for cislunar relative motion; in particular, three-and fourimpulse strategies are reviewed for the far-range rendezvous, and for the close-range renzdezvous, key concepts and several impulsive, targeting strategies available in the literature are reviewed. Blazquez et al [61] looked at the far rendezvous approaches for NRHO and passively safe drift trajectories under a real ephemerides model, employing multiple-shooting and adaptive receding-horizon targeting algorithms, and more recently, Khoury and Howell [62] also looked into solutions to rendezvous and space loitering problems on NRHO and DRO type orbits. Bucchioni, in a series of works, focused on GNC for phasing and rendezvous under 6 DoF models [63][64][65].…”

Section: Introductionmentioning

confidence: 99%

Relative Dynamics and Modern Control Strategies for Rendezvous in Libration Point Orbits

et al. 2022

View full text Add to dashboard Cite

Deep space missions are recently gaining increasing interest from space agencies and industry, their maximum exponent being the establishment of a permanent station in cis-lunar orbit within this decade. To that end, autonomous rendezvous and docking in multi-body dynamical environments have been defined as crucial technologies to expand and maintain human space activities beyond near Earth orbit. Based on analytical and numerical formulations of the relative dynamics in the Circular Restricted Three Body Problem (CR3BP), a family of optimal, linear and nonlinear, continuous and impulsive, guidance and control techniques are developed for the design of end-to-end rendezvous trajectories between co-orbiting spacecraft in this multi-body dynamical environment. To this end, several modern control techniques are effectively designed and adapted to this problem, with particular emphasis on the design of low cost rendezvous manoeuvres. Finally, the designed hybrid rendezvous strategies, combining both discrete and continuous control techniques, are effectively tested and validated under several start-to-end deep space testbench mission scenarios, where their performance is compared and quantitatively assessed with a set of performance indices.

show abstract

“…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. Blazquez et al (2018) and Blazquez et al (2020) proposed that the natural drift of ephemeris NRHO relative to the reference orbit can be used to achieve far-range rendezvous and docking.…”

mentioning

confidence: 99%

Phasing analysis on DRO with impulsive maneuver

Wang

Zhang

2023

Front. Astron. Space Sci.

View full text Add to dashboard Cite

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.

show abstract

Rendezvous design in a cislunar near rectilinear Halo orbit

Cited by 11 publications

References 12 publications

Rendezvous in cislunar halo orbits: Hardware-in-the-loop simulation with coupled orbit and attitude dynamics

Rendezvous in cislunar halo orbits: Hardware-in-the-loop simulation with coupled orbit and attitude dynamics

Relative Dynamics and Modern Control Strategies for Rendezvous in Libration Point Orbits

Phasing analysis on DRO with impulsive maneuver

Contact Info

Product

Resources

About