EQUULEUS Trajectory Design

Oguri, Kenshiro; Oshima, Koichiro; Campagnola, Stefano; Kakihara, Kota; Ozaki, Naoya; Baresi, Nicola; Kawakatsu, Yasuhiro; Funase, Ryu

doi:10.1007/s40295-019-00206-y

Cited by 38 publications

(15 citation statements)

References 29 publications

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“…Therefore, for the Earth escape that targets an asteroid, the objective of trajectory design is to minimize the initial v ∞M to below 800 m/s. For spacecraft and asteroid capture, the objective is to achieve a final v ∞M smaller than 450 m/s, enabling insertion into a mid-to high-lunar orbit at a ∆v of around 350 m/s or a stable NRHO at 20 m/s [7,28,29]. Another propulsion system launched years later to the Earth-Moon regime can possibly provide this insertion ∆v can while waiting to dock with the returned spacecraft and asteroid.…”

Section: Trajectory Design Objectivesmentioning

confidence: 99%

Capacity of Sun-driven Lunar Swingby Sequences and Their Application in Asteroid Retrieval

Chen¹

2023

Preprint

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For deep-space mission design, the gravity of the Sun and the Moon can be first considered and utilized.Their gravity can provide the energy change for launching spacecraft and retrieving spacecraft as well as asteroids. Regarding an asteroid retrieval mission, it can lead to the mitigation of asteroid hazards and easy exploration and exploitation of the asteroid. This paper discusses the application of the Sun-driven lunar swingby sequence for asteroid missions. Characterizing the capacity of this technique is not only interesting in terms of dynamic insights but also non-trivial for trajectory design. This paper elucidates the capacity of a Sun-driven lunar swingby sequence with the help of the "Swingby-Jacobi" graph. The capacity can be represented by a range of Jacobi integral that encloses around 660 asteroids currently cataloged. To facilitate trajectory design, a database of Sun-perturbed Moon-to-Moon transfers, including multi-revolution cases is generated and employed. Massive trajectory options for spacecraft launch and asteroid capture can then be explored and optimized. Finally, a number of asteroid flyby, rendezvous, sample-return, and retrieval mission options enabled by the proposed technique are obtained.

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Section: Trajectory Design Objectivesmentioning

confidence: 99%

Capacity of Sun-driven Lunar Swingby Sequences and Their Application in Asteroid Retrieval

Chen¹

2023

Preprint

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“…They satisfy the optimality conditions even though many of them experience a lunar flyby inducing the sensitive behavior not only in the state vector but also in the primer vector and its time derivative. Figure 14 amplifies the last duration of the time history of the magnitude of the primer vector and its time derivative of the solution (7). The existence of the nearly singular arc in terms of the primer vector [5], i.e., |p| ≈ 1 for a finite duration, would cause a sensitivity leading to the relatively large number of iterations for the solution reported in Table 4.…”

Section: Converged Solutionsmentioning

confidence: 99%

“…Fig.14(a) Time history of the magnitude of the primer vector and (b) its time derivative with timings of the maneuvers (triangle) around the nearly singular arc (|p| ≈ 1) of the optimal transfer solution(7). Time is measured from the initial node.…”

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confidence: 99%

Regularizing fuel-optimal, multi-impulse trajectories

Oshima

2023

Preprint

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The regularization theory has successfully enabled the removal of gravitational singularities associated with celestial bodies. This paper merges regularizing techniques into a multi-impulse trajectory design framework that requires delicate computations specifically in a fuel minimization problem. Regularized variables based on the Levi-Civita or Kustaanheimo-Stiefel transformation express instantaneous velocity changes in a gradient-based direct optimization method. The formulation removes the notorious singularities associated with null thrust impulses from derivatives of an objective function in the fuel minimization problem. The favorite singularity-free property enables accurate reductions of unnecessary impulses and additions of necessary impulses for local optimal solutions in an automatic manner. Examples of fuel-optimal, multi-impulse trajectories are presented including novel transfer solutions between a near rectilinear halo orbit and a distant retrograde orbit.

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“…The current trend in spacecraft miniaturization technologies is enabling CubeSat missions in lunar environment. Space agencies like NASA, ESA, and JAXA are planning CubeSat missions for lunar scientific investigations such as Lunar Flashlight (Cohen et al, 2020), VMMO (Walker et al, 2018), EQUULEUS (Oguri et al, 2020), and LUMIO (Cipriano et al, 2018).…”

Section: Introductionmentioning

confidence: 99%