Reduced cost mission design using surrogate models

Feldhacker, Juliana D.; Jones, Brandon A.; Doostan, Alireza; Hampton, Jerrad

doi:10.1016/j.asr.2015.11.002

Cited by 9 publications

(6 citation statements)

References 42 publications

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“…Peng and Wang proposed a dynamic metamodel-based optimization method for spacecraft formation reconfiguration on liberation point orbits to achieve fast path planning [182]. Feldhacker et al investigated a samplingbased least-squares regression method to optimize the required velocity increments for rendezvous in spacecraft three-body dynamical systems [183]. Peng et al proposed an adaptive metamodel-based optimization method called the sequential radial basis function for satellite truss structure optimization [184].…”

Section: Satellite Constellation Mdo Problemmentioning

confidence: 99%

Metamodel-based multidisciplinary design optimization methods for aerospace system

Shi

et al. 2021

Astrodyn

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The design of complex aerospace systems is a multidisciplinary design optimization (MDO) problem involving the interaction of multiple disciplines. However, because of the necessity of evaluating expensive black-box simulations, the enormous computational cost of solving MDO problems in aerospace systems has also become a problem in practice. To resolve this, metamodel-based design optimization techniques have been applied to MDO. With these methods, system models can be rapidly predicted using approximate metamodels to improve the optimization efficiency. This paper presents an overall survey of metamodel-based MDO for aerospace systems. From the perspective of aerospace system design, this paper introduces the fundamental methodology and technology of metamodel-based MDO, including aerospace system MDO problem formulation, metamodeling techniques, state-of-the-art metamodel-based multidisciplinary optimization strategies, and expensive black-box constraint-handling mechanisms. Moreover, various aerospace system examples are presented to illustrate the application of metamodel-based MDOs to practical engineering. The conclusions derived from this work are summarized in the final section of the paper. The survey results are expected to serve as guide and reference for designers involved in metamodel-based MDO in the field of aerospace engineering.

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Section: Satellite Constellation Mdo Problemmentioning

confidence: 99%

Metamodel-based multidisciplinary design optimization methods for aerospace system

Shi

et al. 2021

Astrodyn

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“…Additionally, surrogate models (SM) are used for representing nonlinearity of hydrodynamic problems [9]. Therefore, SM, also so-called low fidelity models, are becoming popular [10][11].…”

Section: Introductionmentioning

confidence: 99%

“…SM are successfully used by various researches to optimize wind turbine performance [11][12]. These authors reported that SM are very efficient in comparison with the conventional optimization methods [11][12]. However, the optimization of multi-element hydrofoils for hydrokinetic turbines using SM has not been employed in the literature.…”

Section: Introductionmentioning

confidence: 99%

Surrogate modelling for high-lift multi-element hydrofoil shape optimization of a hydrokinetic turbine blade

Rubio-Clemente¹,

Aguilar²,

Chica³

2020

REPQJ

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The hydrodynamic shape of a blade is one of the most important factors in the design process of a horizontal axis hydrokinetic turbine that influences its performance. The present work is focused on the design and hydrodynamic analysis of a high-lift system using the optimization method of surrogate models and computational fluid dynamics (CFD) analysis. The parameters that affect the amount of the lift and the drag force that a hydrofoil can generate are the gap, the overlap, the flap deflection angle (δ), the flap chord length (C2) and the angle of attack of the hydrofoil (α). These factors were varied to examine the turbine performance in terms of the ratio between the lift (CL) and the drag coefficient (CD), and the minimum negative pressure coefficient (min Cpre) in order to avoid the cavitation inception. For this propose, surrogate models were implemented to analyse the CFD results and find the optimal combination of the design parameters of the high-lift hydrofoil. The traditional Eppler 420 hydrofoil was utilized for the design of the multi-element profile, which was composed of a main element and a flap. The multi-element design selected as optimal had a gap of 2.825 %C1, an overlap of 8.52 %C1, a δ of 19.765˚, a C2 of 42.471 %C1 and a α of-4˚, where C1 refers to the chord length of the main element. In comparison with the traditional Eppler 420 hydrofoil, CL/CD ratio increases from 39.050 to 42.517.

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“…Meantime, these urgent transfer missions truly exist when the spacecraft meets emergency incidents or temporary missions.For example, in pursuit and capturemissions [16][17][18][19], when a spacecraft needs to pursue or intercept anobjective spacecraft that flies in other orbits, the transfer maneuver opportunity is significant. In the near future, some space stations or telescopes may locate on halo orbits of the Sun-Earth/Earth-Moon systems.…”

Section: Introductionmentioning

confidence: 99%

“…For these reasons, the efficiency for on-line designing optimal transfer trajectory has significant value. Furthermore, according to the point of view in thereference [19], the use of as efficient design tool can enable significant time savings when performing in trajectory design over long propagation times, trajectory optimization using massive grid searches, or trade space exploration for exercises in rapid mission design.Based on the above analysis, the main concern of this paper is to find a fast multi-objective design method for transfer trajectory.Besides, a popular tool for constructing the fast optimization method is surrogate model [20][21][22][23][24][25].Thus, an adaptive surrogate model basedmulti-objective optimization method is proposed in this paper.…”

Section: Introductionmentioning

confidence: 99%

A fast multi-objective optimization design method for emergency libration point orbits transfer between the Sun–Earth and the Earth–Moon systems

Wang

Peng

2017

Aerospace Science and Technology

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This paper considers the emergency trajectory design mission of libration point orbit transfer between the Sun-Earth system and the Earth-Moon system. In order to balance the two indexes of transfer time and fuel consumption, Halo orbits and theirinvariant manifolds in the circular restricted three body problem (CRTBP) are combined with low thrust in the bicircular restricted four body problem (BRFBP) to design the transfer trajectories. A fast multi-objective optimization methodbased on surrogate modelwhich is greatly needed especially for emergency transfer missions is proposedto overcome the low-efficacy of original evolutionary multi-objectiveoptimization methods. The advantages of the Sun-Earth manifolds,the Earth-Moon manifoldsand the optimal control methodare fully considered.In the part of numerical simulations, several simple problems with analytical solutions are first employed to validate the proposed fast optimization algorithm,thenthe proposed method is compared with NSGA-II for the same multi-objective transfer problem. Numerical results show that the fast optimization method chooses the expected samplesand has a much higher efficiency than direct multi-objective optimization. The significance of the Sun-Earth manifolds and the Earth-Moon manifolds are considered. Several cases show the complicated relationship between transfer time and fuel consumption.

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Reduced cost mission design using surrogate models

Cited by 9 publications

References 42 publications

Metamodel-based multidisciplinary design optimization methods for aerospace system

Metamodel-based multidisciplinary design optimization methods for aerospace system

Surrogate modelling for high-lift multi-element hydrofoil shape optimization of a hydrokinetic turbine blade

A fast multi-objective optimization design method for emergency libration point orbits transfer between the Sun–Earth and the Earth–Moon systems

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