An Inflationary Differential Evolution Algorithm for Space Trajectory Optimization

Vasile, Massimiliano; Minisci, Edmondo; Locatelli, Marco

doi:10.1109/tevc.2010.2087026

Cited by 102 publications

(104 citation statements)

References 22 publications

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“…Remark 2: Even though the general conditions for global convergence of evolutionary algorithms are established in [48], it cannot be analytically shown that DE meets these conditions [49] and converges to the global solution of (16). Moreover, in [48], no specific algorithm that meets these conditions is proposed.…”

Section: B Differential Evolution Based Estimationmentioning

confidence: 99%

“…Moreover, in [48], no specific algorithm that meets these conditions is proposed. Although in [49], a variation of DE is proposed, it is indicated in [49] that this new approach also does not guarantee the global convergence of the DE algorithm. Nevertheless, by appropriately selecting the DE parameters, in our extensive simulations, we have observed the proposed DE estimator to always converge to the true values of timing and frequency offsets as described in Sections IV-C and VI-A.…”

Section: B Differential Evolution Based Estimationmentioning

confidence: 99%

See 1 more Smart Citation

Transceiver Design for Distributed STBC Based AF Cooperative Networks in the Presence of Timing and Frequency Offsets

Nasir

Mehrpouyan

Durrani

et al. 2013

IEEE Trans. Signal Process.

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Abstract-In multi-relay cooperative systems, the signal at the destination is affected by impairments such as multiple channel gains, multiple timing offsets (MTOs), and multiple carrier frequency offsets (MCFOs). In this paper we account for all these impairments and propose a new transceiver structure at the relays and a novel receiver design at the destination in distributed space-time block code (DSTBC) based amplifyand-forward (AF) cooperative networks. The Cramér-Rao lower bounds and a least squares (LS) estimator for the multi-parameter estimation problem are derived. In order to significantly reduce the receiver complexity at the destination, a differential evolution (DE) based estimation algorithm is applied and the initialization and constraints for the convergence of the proposed DE algorithm are investigated. In order to detect the signal from multiple relays in the presence of unknown channels, MTOs, and MCFOs, novel optimal and sub-optimal minimum mean-square error receiver designs at the destination node are proposed. Simulation results show that the proposed estimation and compensation methods achieve full diversity gain in the presence of channel and synchronization impairments in multi-relay AF cooperative networks.Index Terms-Cooperative communication, amplify-andforward (AF), Cramér-Rao lower bound (CRLB), differential evolution (DE), distributed space-time block code (DSTBC), receiver design.

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Section: B Differential Evolution Based Estimationmentioning

confidence: 99%

Section: B Differential Evolution Based Estimationmentioning

confidence: 99%

Transceiver Design for Distributed STBC Based AF Cooperative Networks in the Presence of Timing and Frequency Offsets

Nasir

Mehrpouyan

Durrani

et al. 2013

IEEE Trans. Signal Process.

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show abstract

“…evolutionary computing (EC) and optimization has since emerged as a means for dealing with highly constrained mission profiles for primarily interplanetary trajectories. Evolutionary methods utilized have included genetic algorithms [2,3], particle swarm optimization [4], monotonic basin hopping [5], simulated annealing [6], and differential evolution [7]. To a lesser extent, EC methods have also been leveraged for in-orbit trajectory planning about planets [8][9][10].…”

Section: Introductionmentioning

confidence: 99%

“…Olds and Kluever [17] also focused on interplanetary trajectory design, analyzing the effects of altered DE tuning parameters of four interplanetary trajectory test problems. A derivative of DE was proposed by Vasile et al [7] that added a localized population restart to DE reminiscent of monotonic basin hopping. Vasile and Locatelli [18] also applied elements of search similar to DE in a domain decomposition search approach to interplanetary trajectory design with success.…”

Section: Introductionmentioning

confidence: 99%

Evolutionary Approach to Lambert’s Problem for Non-Keplerian Spacecraft Trajectories

Hinckley

Hitt

2017

Aerospace

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Abstract:In this paper, we use differential evolution (DE), with best-evolved results refined using a Nelder-Mead optimization, to solve boundary-value complex problems in orbital mechanics relevant to low Earth orbits (LEO). A class of Lambert-type problems is examined to evaluate the performance of this evolutionary method in its application to solving nonlinear boundary value problems (BVP) arising in mission planning. In this method, we evolve impulsive initial velocity vectors giving rise to intercept trajectories that take a spacecraft from given initial position in space to specified target position. The positional error of the final position is minimized subject to time-of-flight and/or energy (fuel) constraints. The method is first validated by demonstrating its ability to recover known analytical solutions obtainable with the assumption of Keplerian motion; the method is then applied to more complex non-Keplerian problems incorporating trajectory perturbations arising in low Earth orbit (LEO) due to the Earth's oblateness and rarefied atmospheric drag. The viable trajectories obtained for these challenging problems demonstrate the ability of this computational approach to handle Lambert-type problems with arbitrary perturbations, such as those occurring in realistic mission trajectory design.

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“…The resulting algorithm has been demonstrated to out-perform both DE and MBH on some difficult space trajectory design problems, for instance those where the search space has a (multi) funnel-like structure. 7 The main features of the IDEA algorithm are reported in depth by Vasile et al;…”

mentioning

confidence: 99%

Ascent Trajectory Optimisation for a Single-Stage-to-Orbit Vehicle with Hybrid Propulsion

Pescetelli¹,

Minisci²,

Maddock³

et al. 2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

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This paper addresses the design of ascent trajectories for a hybrid-engine, high performance, unmanned, single-stage-to-orbit vehicle for payload deployment into low Earth orbit. A hybrid optimisation technique that couples a population-based, stochastic algorithm with a deterministic, gradient-based technique is used to maximize the final vehicle mass in low Earth orbit after accounting for operational constraints on the dynamic pressure, Mach number and maximum axial and normal accelerations. The control search space is first explored by the population-based algorithm, which uses a single shooting method to evaluate the performance of candidate solutions. The resultant optimal control law and corresponding trajectory are then further refined by a direct collocation method based on finite elements in time. Two distinct operational phases, one using an air-breathing propulsion mode and the second using rocket propulsion, are considered. The presence of uncertainties in the atmospheric and vehicle aerodynamic models are considered in order to quantify their effect on the performance of the vehicle. Firstly, the deterministic optimal control law is re-integrated after introducing uncertainties into the models. The proximity of the final solutions to the target states are analysed statistically. A second analysis is then performed, aimed at determining the best performance of the vehicle when these uncertainties are included directly in the optimisation. The statistical analysis of the results obtained are summarized by an expectancy curve which represents the probable vehicle performance as a function of the uncertain system parameters. This analysis can be used during the preliminary phase of design to yield valuable insights into the robustness of the performance of the vehicle to uncertainties in the specification of its parameters.

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An Inflationary Differential Evolution Algorithm for Space Trajectory Optimization

Cited by 102 publications

References 22 publications

Transceiver Design for Distributed STBC Based AF Cooperative Networks in the Presence of Timing and Frequency Offsets

Transceiver Design for Distributed STBC Based AF Cooperative Networks in the Presence of Timing and Frequency Offsets

Evolutionary Approach to Lambert’s Problem for Non-Keplerian Spacecraft Trajectories

Ascent Trajectory Optimisation for a Single-Stage-to-Orbit Vehicle with Hybrid Propulsion

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