Preliminary Capture Trajectory Design for Europa Tomography Probe

Federici, Lorenzo; Zavoli, Alessandro; Colasurdo, Guido

doi:10.1155/2018/6890173

Cited by 11 publications

(9 citation statements)

References 17 publications

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“…The solution of the resulting constrained global optimization problem is carried out by an in-house code named "Evolutionary Optimization at Sapienza" (EOS) [28], which implements a selfadaptive, ε-constrained, partially restarted differential evolution algorithm, with a synchronous island-model to handle multiple subpopulations as parallel processes, with sporadic migrations of individuals between them. EOS has been successfully applied to a broad range of unconstrained and constrained space trajectory optimization problems, as multiple gravity-assist trajectories [29,30], rocket ascent trajectories [31], and multirendezvous missions [32].…”

Section: B Global Optimization Algorithmmentioning

confidence: 99%

Integrated Optimization of First-Stage SRM and Ascent Trajectory of Multistage Launch Vehicles

Federici

Zavoli

Colasurdo

et al. 2021

Journal of Spacecraft and Rockets

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Section: B Global Optimization Algorithmmentioning

confidence: 99%

Integrated Optimization of First-Stage SRM and Ascent Trajectory of Multistage Launch Vehicles

Federici

Zavoli

Colasurdo

et al. 2021

Journal of Spacecraft and Rockets

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“…EOS is an inhouse optimization code for continuous-variable problems, which implements an improved self-adaptive, partially restarted Differential Evolution (DE) algorithm, with a synchronous island model to handle multiple populations in parallel. EOS was developed in the contest of the Global Trajectory Optimization Competitions [49,50] and has proven to be a flexible and high-performance algorithm, able to successfully cope with a broad range of real-world unconstrained and constrained space trajectory optimization problems [51,52]. The values of the hyperparameters used in this work are reported in Table 1.…”

Section: Inner-levelmentioning

confidence: 99%

Evolutionary Optimization of Multirendezvous Impulsive Trajectories

Federici

Zavoli

Colasurdo

2021

International Journal of Aerospace Engineering

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This paper investigates the use of evolutionary algorithms for the optimization of time-constrained impulsive multirendezvous missions. The aim is to find the minimum- Δ V trajectory that allows a chaser spacecraft to perform, in a prescribed mission time, a complete tour of a set of targets, such as space debris or artificial satellites, which move on the same orbital plane at slightly different altitudes. For this purpose, a two-level design approach is pursued. First, an outer-level combinatorial problem is defined, dealing with the simultaneous optimization of the sequence of targets and the rendezvous epochs. The suggested approach is first tested by assuming that all transfer legs last exactly the same amount of time; then, the time domain is discretized over a finer grid, allowing a more appropriate sizing of the time window allocated for each leg. The outer-level problem is solved by an in-house genetic algorithm, which features an effective permutation-preserving solution encoding. A simple, but fairly accurate, heuristic, based on a suboptimal four-impulse analytic solution of the single-target rendezvous problem, is used when solving the combinatorial problem for a fast guess at the transfer cost, given the departure and arrival epochs. The outer-level problem solution is used to define an inner-level NLP problem, concerning the optimization of each body-to-body transfer leg. In this phase, the encounter times are further refined. The inner-level problem is tackled through an in-house multipopulation self-adaptive differential evolution algorithm. Numerical results for case studies including up to 20 targets with different time grids are presented.

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“…In the early phase of this study, a direct EOI maneuver requiring an average ΔV of at least 3 km/s was considered. Since the system mass budget resulting from this mission baseline was well over 500 kg (thus against the overall idea of a small probe), we referenced the propulsion system design to the pre-insertion flyby trajectory designed specifically for ETP in [30]. Thus, after being released by the main spacecraft, ETP will perform 8 flybys of Europa and 1 of Ganymede until achieving a 6:5 resonant orbit with Europa.…”

Section: Pre-insertion and Europa Orbit Insertion (Eoi)mentioning

confidence: 99%

A small spacecraft to probe the interior of the Jovian moon Europa: Europa Tomography Probe (ETP) system design

et al. 2020

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We propose the system design of a small orbiter of the Jovian moon Europa (Europa Tomography Probe, ETP in short) aimed at unveiling its interior structure. ETP is conceived as a piggyback probe of a larger spacecraft to the Jovian system (such as Europa Clipper). Its payload comprises only a magnetometer and transponder. The former will be used to measure the time-varying, induction magnetic field of the moon at different orbital and rotational frequencies, a measurement inaccessible to a flyby spacecraft. An Inter-Satellite Link (ISL) between ETP and the main spacecraft, enabled by the on-board transponder, will be used to accurately determine Europa's gravity field, rotational state and tidal deformation. By combining magnetic and gravity field measurements, ETP could characterize the interior structure of Europa with an accuracy only attainable by a lowaltitude orbiter, thus constraining the thickness and conductivity of the subsurface ocean. Following the announcement that a 250-300-kg mass allowance was available on the upcoming NASA Europa Clipper spacecraft, we propose ETP's mission and spacecraft design assuming Clipper's nominal trajectory as a baseline. The concept can be adapted to a class of missions to the Jovian and Saturnian systems based upon a mother-daughter spacecraft system. The spacecraft design has been pursued under the philosophy of determining the minimum required total mass and volume that allows to meet the scientific requirements, rather than finding out what science return could be obtained with pre-assigned system constraints. Since ETP shall autonomously reach its final orbit, the propulsion system has been one of the primary focuses. The radiation analysis has also been essential because the shielding structure affects both the mission duration and the mass budget. We show that the ETP concept could be, indeed, technically feasible with an overall system mass budget just above 250 kg, thus providing a valuable yet affordable augmentation to a larger flyby mission to Europa.

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Preliminary Capture Trajectory Design for Europa Tomography Probe

Cited by 11 publications

References 17 publications

Integrated Optimization of First-Stage SRM and Ascent Trajectory of Multistage Launch Vehicles

Integrated Optimization of First-Stage SRM and Ascent Trajectory of Multistage Launch Vehicles

Evolutionary Optimization of Multirendezvous Impulsive Trajectories

A small spacecraft to probe the interior of the Jovian moon Europa: Europa Tomography Probe (ETP) system design

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