Helicopter Shipboard Landing Simulation Including Wind, Deck Motion and Dynamic Ground Effect

2020 ◽  
pp. 1-20
Author(s):  
Abhinav Sharma ◽  
Ashwani Padthe ◽  
Peretz P. Friedmann
Keyword(s):  
Ground Effect ◽  
Shipboard Landing

scholarly journals Energy Extraction Performance of Tandem Ground-effect Hydrofoils

2021 ◽  
Vol 809 (1) ◽  
pp. 012001
Author(s):  
Hao Yang ◽  
Guanghua He ◽  
Weijie Mo ◽  
Wei Wang
Keyword(s):  
Ground Effect ◽  
Energy Extraction ◽  
Extraction Performance

scholarly journals Conceptual design of a novel Unmanned Ground Effect Vehicle

2021 ◽  
Vol 1024 (1) ◽  
pp. 012058
Author(s):  
C Papadopoulos ◽  
D Mitridis ◽  
K Yakinthos
Keyword(s):  
Conceptual Design ◽  
Ground Effect

Aerodynamic interference test of quad tilt rotor aircraft in wind tunnel

2019 ◽  
Vol 233 (15) ◽  
pp. 5553-5566 ◽  
Author(s):  
Kun Chen ◽  
Zhiwei Shi ◽  
Shengxiang Tong ◽  
Yizhang Dong ◽  
Jie Chen
Keyword(s):  
Wind Tunnel ◽  
Reference Value ◽  
Ground Effect ◽  
Open Loop ◽  
Force Balance ◽  
Scale Model ◽  
Operating Condition ◽  
Tilt Rotor ◽  
Interference Test ◽  
Aerodynamic Interference

There is an obvious aerodynamic interference problem that occurs for a quad tilt rotor in near-ground hovering or in the conversion operating condition. This paper presents an aerodynamic interference test of the quad tilt rotor in a wind tunnel. A 1:35 scale model of the quad tilt rotor is used in this test. To substitute for the ground, a moveable platform is designed in a low-speed open-loop wind tunnel to simulate different flight altitudes of the quad tilt rotor in hovering or forward flight. A rod six-component force balance is used to measure the loads on the aircraft, and the flow field below the airframe is captured using particle image velocimetry. The experimental results show that the ground effect is significant when the hover height above the ground is less than the rotor diameter of the quad tilt rotor aircraft, and the maximum upload of the airframe is approximately 12% of the total vertical thrust with the appearance of obvious fountain flow. During the conversion operating condition, the upload of the airframe is reduced compared with that in the hovering state, which is affected by rotor wake and incoming flow. The aerodynamic interference test results of the quad tilt rotor aircraft have important reference value in power system selection, control system design, and carrying capacity improvement with the advantage of ground effect.

scholarly journals Hovering Performance of a Rotor in an Inclined and Partial Ground Effect

2003 ◽  
Vol 51 (595) ◽  
pp. 433-440 ◽  
Author(s):  
Naohiro Iboshi ◽  
Noriaki Itoga ◽  
Yasutaka Hayata ◽  
J. V. R. Prasad
Keyword(s):  
Ground Effect
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