Towards real-time pilot-in-the-loop CFD simulations of helicopter/ship dynamic interface

Oruc, Ilker; Horn, Joseph F.; Shipman, Jeremy; Polsky, Susan

doi:10.1142/s179396231743005x

Cited by 27 publications

(11 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…To take one example, it is quite difficult and potentially dangerous to land a helicopter on the windy flight deck of an aircraft carrier, due to the complexity and speed of the air flow. In his 2017 PhD thesis [15], Oruc noted that "Especially, when the aircraft flies in the near vicinity of the superstructure of the ship, the pilot workload increases seriously." He examines the potential for semi-automatic flight control with in the loop CFD.…”

Section: A Applicationsmentioning

confidence: 99%

Fast Stencil-Code Computation on a Wafer-Scale Processor

Rocki¹,

Essendelft²,

Sharapov³

et al. 2020

Preprint

View full text Add to dashboard Cite

The performance of CPU-based and GPUbased systems is often low for PDE codes, where large, sparse, and often structured systems of linear equations must be solved. Iterative solvers are limited by data movement, both between caches and memory and between nodes. Here we describe the solution of such systems of equations on the Cerebras Systems CS-1, a wafer-scale processor that has the memory bandwidth and communication latency to perform well. We achieve 0.86 PFLOPS on a single wafer-scale system for the solution by BiCGStab of a linear system arising from a 7-point finite difference stencil on a 600 × 595 × 1536 mesh, achieving about one third of the machine's peak performance. We explain the system, its architecture and programming, and its performance on this problem and related problems. We discuss issues of memory capacity and floating point precision. We outline plans to extend this work towards full applications.

show abstract

Section: A Applicationsmentioning

confidence: 99%

Fast Stencil-Code Computation on a Wafer-Scale Processor

Rocki¹,

Essendelft²,

Sharapov³

et al. 2020

Preprint

View full text Add to dashboard Cite

show abstract

“…However, in a rotor-fuselage aerodynamic layout design, for example, where the simulation of a rotor-fuselage interaction is necessary [7], the design variables are often the position of the rotor relative to the fuselage or the geometry of the fuselage, rather than the geometry of the rotor itself. Similarly, the simulation of complex interactions arising from the ship-rotor wake for different wind angles and shipboard landing locations is another situation where application may be performed [8][9][10]. In the simulation of such problems, where the geometry of blades is constant, it is often necessary to have unstructured meshes to fit the complex fuselage/ship geometry and sufficient resolution to predict a rotor-induced downwash flow.…”

Section: Introductionmentioning

confidence: 99%

Combination of Advanced Actuator Line/Disk Model and High-Order Unstructured Finite Volume Solver for Helicopter Rotors

Yang,

Li,

Pei

2024

Aerospace

View full text Add to dashboard Cite

In the research field of rotorcraft aerodynamics, there are two fundamental challenges: resolving the complex vortex structures in rotor wakes and representing the moving rotor blades in the ambient airflow. In this paper, we address the first challenge by utilizing a third-order unstructured finite volume solver, which exhibits lower numerical dissipation than its second-order counterpart. This allows for sufficient resolution of small vortex structures on relatively coarse meshes. With this flow solver, the second challenge is addressed by modeling each rotor as an actuator disk (i.e., the actuator disk model (ADM)) or modeling each blade as an actuator line (i.e., the actuator line model (ALM)). Both of the two models are equipped with an improved tip loss correction, which is introduced in detail in the methodology section. In the section of numerical experiments, the numerical convergence properties of the two types of solvers have been compared in the case of two-dimensional infinite wing. In addition, the relationship between the ALM and the lifting line theory is discussed in the cases of fixed-wing calculations. Another goal of these cases is to validate the tip loss correction presented. The validation of the ALM/ADM and comparisons of computational efficiency are also demonstrated in simulations involving both hover and forward flight rotors. It was found that the combination of the third-order finite volume solver and the ALM/ADM with the improved tip loss correction presents an efficient way of performing the aerodynamic analysis of rotor-induced downwash flow.

show abstract

“…However, early studies were almost circumvented by the generalization analysis of the isolated ship airwakes. To compensate for this defect, the numerical simulation of the coupling ship-helicopter has been implemented and analyzed by some research (Crozon et al, 2014;Oruc et al, 2015;Rajmohan et al, 2015;Zhang et al, 2009). Zhang and Su (2011) which performed an investigation by Euler solution on the influence of ship airflow on a Bell 412 helicopter model.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the unsteady coupling airflow impact of a full-scale warship with a helicopter during shipboard landing

Chang

Chuang

et al. 2020

Engineering Applications of Computational Fluid Mechanics

View full text Add to dashboard Cite

In this paper, a comprehensive computational modeling study of the unsteady aerodynamic environment around a warship with a helicopter is performed. An experimental validation exercise is also conducted, comparing computational fluid dynamics (CFD) results of the airwake calculated for a reduced-scale model of the isolated Landing Helicopter Assault (LHA) model with high-quality particle image velocimetry experimental data provided by the NASA AMES Research Center. Comparisons of the results generally obtain agreement, indicating that the CFD numerical method is able to resolve the large-scale turbulent airflow. Building on this, a numerical simulation of a real Robin helicopter, immersed in the unsteady airwakes of a full-scale Amphibious Assault Ship (AAS), is performed. The aerodynamic simulation of the influence on the coupled airflow of warship-helicopter is explored and compared with that of the solitary ship airflow field and the superposition airwakes, where the vortex patterns and pressure on the ship surface, as well as the velocity distribution, are circumvented. As a further step, dynamic landing analysis of the airflow field for a shipborne helicopter is implemented at an important location through the landing path for headwind. The aerodynamic characteristics of a helicopter during a flight deck landing are also explored for the unsteady ship airwakes impacting on rotor force during shipboard landings. In addition, different shipboard landing paths of the helicopter are comparatively investigated for obtaining an optimal landing path decision. The present study demonstrates an effective aerodynamic analysis and robust numerical approach, which creates a solid foundation supporting further alternative evaluations of ship airflow fields.

show abstract

Towards real-time pilot-in-the-loop CFD simulations of helicopter/ship dynamic interface

Cited by 27 publications

References 14 publications

Fast Stencil-Code Computation on a Wafer-Scale Processor

Fast Stencil-Code Computation on a Wafer-Scale Processor

Combination of Advanced Actuator Line/Disk Model and High-Order Unstructured Finite Volume Solver for Helicopter Rotors

Numerical investigation of the unsteady coupling airflow impact of a full-scale warship with a helicopter during shipboard landing

Contact Info

Product

Resources

About