Aeroelastic response of rocket nozzles to asymmetric thrust loading

Zhao, Xiang; Bayyuk, Sami; Zhang, Sijun

doi:10.1016/j.compfluid.2013.01.022

Cited by 16 publications

(6 citation statements)

References 25 publications

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“…To optimize the shape of the nozzle to provide the maximum thrust, the results of the simulation of flows of an inviscid and viscous compressible gas were applied in [9,10]. The flow in the nozzle and the stress-strain state of the nozzle walls (coupled modeling) associated with the occurrence of asymmetric loads were discussed in [13].…”

Section: Introductionmentioning

confidence: 99%

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

2021

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The optimal design of the thrust vector control system of solid rocket motors (SRMs) is discussed. The injection of a supersonic underexpanded gas jet into the diverging part of the rocket engine nozzle is considered, and multiparameter optimization of the geometric shape of the injection nozzle and the parameters of jet injection into a supersonic flow is developed. The turbulent flow of viscous compressible gas in the main nozzle and injection system is simulated with the Reynolds-averaged Navier–Stokes (RANS) equations and shear stress transport (SST) turbulence model. An optimization procedure with the automatic generation of a block-structured mesh and conjugate gradient method is applied to find the optimal parameters of the problem of interest. Optimization parameters include the pressure ratio of the injected jet, the angle of inclination of the injection nozzle to the axis of the main nozzle, the distance of the injection nozzle from the throat of the main nozzle and the shape of the outlet section of the injection nozzle. The location of injection nozzle varies from 0.1 to 0.9 with respect to the length of the supersonic part of the nozzle; the angle of injection varies from 30 to 160 degrees; and the shape of the outlet section of the injection nozzle is an ellipse with an aspect ratio that varies from 0.1 to 1. The computed fluid flow in the combustion chamber is compared with experimental and computational results. The dependence of the thrust as a function of the injection parameters is obtained, and conclusions are made about the effects of the input parameters of the problem on the thrust coefficient.

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Section: Introductionmentioning

confidence: 99%

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

2021

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“…Compressible fluid-structure interaction (FSI) occurs in a broad range of technical applications involving, e.g., nonlinear aeroelasticity [16,42] and shock-induced deformations of rocket nozzles [23,55]. The numerical modeling and simulation of compressible FSI can be challenging, in particular if an accurate representation of the structural interface within the fluid solver and a consistent coupling of both subdomains is required.…”

Section: Introductionmentioning

confidence: 99%

A cut-cell finite volume – finite element coupling approach for fluid–structure interaction in compressible flow

Pasquariello

Hammerl

Örley

et al. 2016

Journal of Computational Physics

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We present a loosely coupled approach for the solution of fluid-structure interaction problems between a compressible flow and a deformable structure. The method is based on staggered Dirichlet-Neumann partitioning. The interface motion in the Eulerian frame is accounted for by a conservative cut-cell Immersed Boundary method. The present approach enables subcell resolution by considering individual cut-elements within a single fluid cell, which guarantees an accurate representation of the time-varying solid interface. The cut-cell procedure inevitably leads to non-matching interfaces, demanding for a special treatment. A Mortar method is chosen in order to obtain a conservative and consistent load transfer. We validate our method by investigating two-dimensional test cases comprising a shock-loaded rigid cylinder and a deformable panel. Moreover, the aeroelastic instability of a thin plate structure is studied with a focus on the prediction of flutter onset. Finally, we propose a three-dimensional fluid-structure interaction test case of a flexible inflated thin shell interacting with a shock wave involving large * Corresponding author.

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“…These improvements were not realized until 2008, when Zhang, et al [5] embarked on probably the first coupled CFD/CSD methodology for aeroelastic nozzle study, by coupling among a full NavierStokes solver CFD-FASTRAN, a CSD code FEM-STRESS, and an interface code MDICE, on a quasi-steady, twodimensional nozzle. In 2013, the same methodology was further demonstrated to show aeroelastic deformation of nozzle wall by Zhao et al [6], on a quasi-steady, three-dimensional analysis of a J-2S nozzle for 0.1818 s of elapsed time. These developments represent advances over earlier simple aeroelastic nozzle analyses.…”

Section: Introductionmentioning

confidence: 80%

“…While examining the recent aeroelastic analyses [5,6], the CFD and CSD computations were carried out in different codes and those codes were only connected through an interface code, thus the analyses can only be categorized as loosely coupled aeroelastic solutions [6]. Very recently, Wang et al [7] made an effort to implement the necessary CSD formulations directly into a CFD code, thereby providing a tightly coupled solution of the two-way fluid and structure interactions and potentially be more computationally efficient and accurate.…”

Section: Introductionmentioning

confidence: 99%

“…With the advances in aeroelastic modeling of nozzle side loads [5,6], and the recognition of the importance of fluid-structure interaction on transient nozzle physics, there is a need to improve our design and analysis methodology by considering the aeroelastic modeling. While examining the recent aeroelastic analyses [5,6], the CFD and CSD computations were carried out in different codes and those codes were only connected through an interface code, thus the analyses can only be categorized as loosely coupled aeroelastic solutions [6].…”

Section: Introductionmentioning

confidence: 99%

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Aeroelastic Response of Rocket Nozzles Subected to Combined Thrust and Side Loads

Zhang

Shotorban

Pohly

et al. 2015

22nd AIAA Computational Fluid Dynamics Conference

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Lateral nozzle forces are known to cause severe structural damage to any new rocket engine in development during test. While three-dimensional, transient, turbulent, chemically reacting computational fluid dynamics methodology has been demonstrated to capture major side load physics with rigid nozzles, hot-fire tests often show nozzle structure deformation during major side load events. Such deformation leads to structural damages if appropriate structural strengthening measures are not taken. The modeling picture is incomplete without the aeroelastic coupling to address the two-way responses between the structure and fluid. The present work takes into account the aeroelastic coupling for side loads predictions. A loosely coupled method for fluid structural interaction is employed to study the role of the coupling. Two side load cases were computed and are comparatively analyzed for the J-2S nozzle, one case with flexible walls and the other with rigid walls. It is found that aeroelastic coupling has significant effects on the side loads in the nozzle.

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Aeroelastic response of rocket nozzles to asymmetric thrust loading

Cited by 16 publications

References 25 publications

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

A cut-cell finite volume – finite element coupling approach for fluid–structure interaction in compressible flow

Aeroelastic Response of Rocket Nozzles Subected to Combined Thrust and Side Loads

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