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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2017, Vol. 38 ›› Issue (7): 520853-520853.doi: 10.7527/S1000-6893.2017.120853

• Special Column of Helicopter Technology • Previous Articles     Next Articles

Numerical simulatin of coupled flow field of helicopter/ship

SU Dacheng1, SHI Yongjie1, XU Guohua1, ZONG Kun2   

  1. 1. National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. System Engineering Research Institute, China State Shipbuilding Corporation, Beijing 100036, China
  • Received:2016-10-13 Revised:2016-11-05 Online:2017-07-15 Published:2017-03-09
  • Supported by:

    National Key Laboratory Foundation of Science and Technology on Rotorcraft Aeromechanics (6142220010301)

Abstract:

A computational method based on Reynolds-Averaged Navier-Stokes (RANS) equations is developed for the study of aerodynamic interaction between helicopter and ship, wherein ROE-MUSCL scheme is used to reconstruct the flux at the interface, and k-ε turbulence model is used to improve the simulation precision for flow structure. Actuator disk method is used to simulate the main rotor and tail. A scaled LPD-17 ship and ROBIN helicopter are then used to simulate the coupled flow field. The coupled flow field characteristics are analyzed, inlucing vorticity, velocity and pressure fields. Analysis results indicate that when the freestream velocity is greater than 4 m/s, Reynolds number of ship flowfield comes into the prospective area of Reynolds number the normalized velocity components of the ship flow field remain unchanged; during the landing process, the main rotor will interact with the large recirculation zone and the deck-edge vortices, and these interactions as well as ground effect cause the rotor thrust to oscillate, and the oscillation shows a regularity of increase first and then decrease. When the landing spot moves to the stern, the effect of the recirculation zone diminishes, thus causing reduction of the amplitude of thrust oscillation. Simulation of the interaction between full aircraft and ship is conducted. Results show that fuselage and tail have slightly influence on the characteristics of the main flow field; therefore, the coupled flow field of rotor/ship can be used to analyze the safety during shipborne operations, and the computation time can thus be shortened significantly.

Key words: helicopter, ship, ship airwake, actuator disk method, shipborne operation

CLC Number: