Transactions of Nanjing University of Aeronautics & Astronautics
Dynamic Behavior of Missiles Released from a Helicopter with Downwash Effect
- Article
- Figures
- Metrics
- Preview PDF
- Reference
- Related
- Cited by
- Materials
Abstract:
This study is dedicated to numerically investigate the dynamic behavior of a missile released from a helicopter under the influence of downwash from the rotating rotors using AGM-114 Hellfire and UH-60 as the testcase. Simulations are conducted using unsteady Reynolds-averaged Navier-Stokes （URANS） with shear stress transport （SST） k-ω turbulence model， incorporating six-degree-of-freedom （6-DOF） motion and overset grid. Two releasing scenarios， viz.， hover and forward flight， are analyzed under varying missile launch thrust and helicopter forward flight speed. Results reveal that the rotor downwash significantly affects the stability of the missile， particularly during hovering case， where low thrust prolongs wake interaction. In forward flight， the increased airspeed can in principle reduce wake influence but introduces asymmetrical aerodynamic effects on the trajectory of the missile. The findings offer guidance for missile release and launch planning in rotorcraft operations.
Keywords:
Project Supported:
This work was supported by the National Natural Science Foundation of China （No.11602200）. The authors would like to acknowledge the following individuals for their assistance： XIAO Tianhang， ZHI Haolin， ZHU Zhenhao， XIAO Jiliang， ZHENG Li， LIN Yinnan and CHEN Meili， all affiliated with the Nanjing University of Aeronautics and Astronautics （NUAA）.
Clc Number:
V211.3
Articles
Mobile website
