A Mode Based Reduced Order Model for Supersonic Store Separation

Peters, Nicholas; Ekaterinaris, John A.; Wissink, Andrew M.

doi:10.2514/6.2021-2548

Cited by 5 publications

(4 citation statements)

References 24 publications

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“…A similarity law between the separation of a heavy store and the unsteady wind tunnel free flight tests of air-launch rockets was derived, is can be used to the research of the separation of a heavy store [17,18]. A modeling method based reduced order model for external store separation is proposed, which can make high fidelity predictions for both surface pressure and shear stress distributions at minimal computational cost [19,20].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation about the Characteristics of the Store Released from the Internal Bay in Supersonic Flow

Cheng¹,

Si²,

Li³

et al. 2023

Computer Modeling in Engineering &Amp; Sciences

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To understand the influence of the initial release conditions on the separation characteristics of the store and improve it under high Mach number (Ma = 4) flight conditions, the overset grid method and the Realizable k − ε turbulence model coupled with an equation with six degrees of freedom are used to simulate the store released from the internal bay. The motion trajectory and the attitude angle of the store separation under the conditions of different centroid, velocity, height and control measures are given by the calculated result. Through analysis, the position of the centroid will affect the separation of the store, which needs to be considered in the design. Increasing the launching height is conducive to the separation of the store. If the store has an initial velocity, it can leave the internal bay more quickly and reduce the probability of collision with the wall. Cylindrical rod and slanted aft wall control measures can improve the attitude of the store and make the store fall more smoothly.

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Section: Introductionmentioning

confidence: 99%

Numerical Simulation about the Characteristics of the Store Released from the Internal Bay in Supersonic Flow

Cheng¹,

Si²,

Li³

et al. 2023

Computer Modeling in Engineering &Amp; Sciences

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“…Multibody separation has been successfully investigated in numerous studies by means of flight test, wind tunnel test, and numerical simulation [7][8][9][10]. However, it is difficult to consider the aeroelastic effect in the multibody separation in the wind tunnel test, and limited research has been conducted by this approach.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Aeroelasticity Effect on Missile Separation from the Internal Bay

Tian

2023

International Journal of Aerospace Engineering

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There is a strong aerodynamic interference when launching the missile in the embedded mode. During the separation process, the carrier aircraft safety may be threatened due to large slenderness ratio, low structural stiffness, and aeroelasticity effects of the missile. The present study simulates missile separation in the presence of the aeroelasticity effects based on the computational fluid dynamics (CFD), rigid body dynamics (RBD), and computational structure dynamics (CSD) coupling method. A hybrid dynamic grid method consisting of the mixed overset unstructured grid and deformation grid is utilized. In order to verify the accuracy of the coupled numerical method, store separation from a wing and AGARD 445.6 wing flutter are first simulated as two standard test cases. The verification results imply that the present coupled numerical method is reliable and capable in simulation of the aeroelastic effect in missile separation. The influence of aeroelasticity on the separation trajectory of a missile from the internal bay is systematically studied at different states. Numerical results show that aeroelasticity substantially affects the missile angular displacement, while it has a slight impact on the linear displacement of the center of mass. Mach number and flight altitude are two important flight parameters that characterize the aeroelasticity effect on missile separation from the internal bay.

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“…Recent work has shown that these ROMbased surrogate models are able to retain a high degree of fidelity while operating at a minimal computational cost. Examples of areas of ROM application include wake modeling (Ali and Cal, 2020;Zehtabiyan-Rezaie et al, 2022;Hamilton et al, 2018), combustion (Chang et al, 2019), turbine blade modeling (Jin et al, 2017), boundary layer ingestion (Cinquegrana and Vitagliano, 2021), and store separation (Peters et al, 2021(Peters et al, , 2022a(Peters et al, , b, 2023. Work completed by De Cillis et al (2022b) demonstrated the derivation of a DMD-based ROM for rotor wake predictions.…”

Section: Introductionmentioning

confidence: 99%

A data-driven reduced-order model for rotor optimization

Peters¹,

Silva²,

Ekaterinaris³

2023

Wind Energ. Sci.

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Abstract. For rotor design applications, such as wind turbine rotors or urban air mobility (UAM) rotorcraft and flying-car design, there is a significant challenge in quickly and accurately modeling rotors operating in complex, turbulent flow fields. One potential path for deriving reasonably accurate but low-cost rotor performance predictions is available through the application of data-driven surrogate modeling. In this study, an initial investigation is undertaken to apply a proper orthogonal decomposition (POD)-based reduced-order model (ROM) for predicting rotor distributed loads. The POD ROM was derived based on computational fluid dynamics (CFD) results and utilized to produce distributed-pressure predictions on rotor blades subjected to topology change due to variations in the twist and taper ratio. Rotor twist, θ, was varied between 0, 10, 20, and 30∘, while the taper ratio, λ, was varied as 1.0, 0.9, 0.8, and 0.7. For a demonstration of the approach, all rotors consisted of a single blade. The POD ROM was validated for three operation cases: a high-pitch or a high-thrust rotor in hover, a low-pitch or a low-thrust rotor in hover, and a rotor in forward flight at a low speed resembling wind turbine operation with wind shear. Results showed that reasonably accurate distributed-load predictions could be achieved and the resulting surrogate model can predict loads at a minimal computational cost. The computational cost for the hovering blade surface pressure prediction was reduced from 12 h on 440 cores required for CFD to a fraction of a second on a single core required for POD. For rotors in forward flight, cost was reduced from 20 h on 440 cores to less than a second on a single core. The POD ROM was used to carry out a design optimization of the rotor such that the figure of merit was maximized for hovering-rotor cases and the lift-to-drag effective ratio was maximized in forward flight.

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A Mode Based Reduced Order Model for Supersonic Store Separation

Cited by 5 publications

References 24 publications

Numerical Simulation about the Characteristics of the Store Released from the Internal Bay in Supersonic Flow

Numerical Simulation about the Characteristics of the Store Released from the Internal Bay in Supersonic Flow

Investigation of Aeroelasticity Effect on Missile Separation from the Internal Bay

A data-driven reduced-order model for rotor optimization

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