Coupled Flight Dynamics and Computational Fluid Dynamics Simulations of Rotorcraft/Terrain Interactions

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

doi:10.2514/1.c034101

Cited by 16 publications

(2 citation statements)

References 10 publications

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“…But in this AD model, the blade loadings were obtained by the blade element model. Oruc et al [5,18] also used a similar method to simulate the ship-helicopter interactions.…”

Section: Past Workmentioning

confidence: 99%

Numerical Simulation of Fully Coupled Flow-Field and Operational Limitation Envelopes of Helicopter-Ship Combinations

Cao

Qin

Tan

et al. 2022

JMSE

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Landing a helicopter to the ship flight deck is most demanding even for the most experienced pilots and modeling and simulation of the ship-helicopter dynamic interface is a substantially challenging technical problem. In this paper, a coupling numerical method was developed to simulate the fully coupled ship-helicopter flow-field under complete wind-over-deck conditions. The steady actuator disk model based on the momentum source approach and the resolved blade method based on the moving overset mesh method were employed to model the rotor. Two different ship-helicopter combinations were studied. The helicopter flight mechanics model was established and then the influences of coupled airwake on the helicopter were analyzed. Finally, based on the derived rejection criterion of safe landing and the developed numerical method, the flight envelopes for these two ship-helicopter combinations were predicted. The steady actuator disk model was found to be effective in the study of helicopter operations in the shipboard environment. The calculated flight envelopes indicate that an appropriate wind direction angle is beneficial to increasing the allowable maximum wind speed and the operating boundary is affected by the rotation direction of the main rotor.

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“…But in this AD model, the blade loadings were obtained by the blade element model. Oruc et al [5,18] also used a similar method to simulate the ship-helicopter interactions.…”

Section: Past Workmentioning

confidence: 99%

Numerical Simulation of Fully Coupled Flow-Field and Operational Limitation Envelopes of Helicopter-Ship Combinations

Cao

Qin

Tan

et al. 2022

JMSE

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show abstract

“…Then, the local velocity data is computed by CFD solver and fed back to the flight dynamics simulation (Refs. [6][7][8]. Depending on the computational cost of the numerical algorithm, this approach might be used in real time flight simulation.…”

Section: Introductionmentioning

confidence: 99%

Towards a Wind Tunnel Testing Environment for Rotorcraft Operations Close to Obstacles

Taymourtash¹,

Zagaglia²,

Zanotti³

et al. 2019

Proceedings of the Vertical Flight Society 75th Annual Forum

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The correct identification of the aerodynamic loads due to interaction between rotorcraft and obstacles requires to run computationally intensive numerical models characterized by a high level of uncertainty. Wind tunnel data can be used as a source of information to improve those models. The present paper investigates the aerodynamic interaction of a helicopter and ship airwake exploiting wind tunnel data. A series of wind tunnel experiment, using a scaled helicopter model and Simple Frigate Shape 1, has been performed to measure forces and moments acting on the rotor, while the helicopter is approaching the flight deck. In addition, the velocity components along the longitudinal symmetry plane of the rotor have been visualized using PIV technique. With the rotor positioned at the starting point of the landing trajectory, the load measurements are used to modify the distribution of the inflow over the rotor in multibody simulation environment, in order to generate same loads, including thrust, torque and in-plane moments. Then, an identification algorithm is developed to capture the effect of ship airwake on the rotor loads during the maneuvers, modeling it as an external gust to the rotor inflow. The gust velocity is obtained through an optimization algorithm with the objective of generating same load coefficients as the experiment. The simulation results show that the same load coefficients as the experiment can be generated by implementing a linear gust over the rotor with a magnitude that changes as the rotor moves through the wake of ship. The experiment showed that this test setup could be used for identification of aerodynamic interaction to be used for maneuver analysis.

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Modeling and analysis of landing collision dynamics for a shipborne helicopter

et al. 2021

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Coupled Flight Dynamics and Computational Fluid Dynamics Simulations of Rotorcraft/Terrain Interactions

Cited by 16 publications

References 10 publications

Numerical Simulation of Fully Coupled Flow-Field and Operational Limitation Envelopes of Helicopter-Ship Combinations

Numerical Simulation of Fully Coupled Flow-Field and Operational Limitation Envelopes of Helicopter-Ship Combinations

Towards a Wind Tunnel Testing Environment for Rotorcraft Operations Close to Obstacles

Modeling and analysis of landing collision dynamics for a shipborne helicopter

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