Numerical Investigations on Wedge Control of Separation of a Missile from an Aircraft

  • Shiquan Zhu Nanjing University of Science and Technology
  • Zhengui Huang Nanjing University of Science and Technology
  • Yongjie Gou Aerospace System Engineering Shanghai
  • Qizhong Tang China North Industries Group Corporation
  • Zhihua Chen Nanjing University of Science and Technology
Keywords: Missile separation, Flow control, Wedge device, Internal weapons bay, Six-degrees-of-freedom

Abstract

To make the missile safely separate from the internal weapons bay, a wedge flow control device is mounted on the front of the bay to control the variation of flow during the separation. The numerical simulations of missile separation without and with wedge flow control device under different sizes are carried out. The flow fields of different separation processes are obtained and discussed; the aerodynamic parameters and trajectory parameters of missile of different cases are illustrated and compared. Results show that, the wedge flow control device can accelerate the missile separation and has the effect of regulating the angular motion of missile. The influence of the wedge height is stronger than that of its length on the center of gravity motion and angular motion of missile.

Author Biographies

Shiquan Zhu, Nanjing University of Science and Technology
Mr Shiquan Zhu is currently pursuing his PhD in the Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing, China. His research interests include: computational fluid dynamics of supersonic flow, multi-body separation problem and fluid-structure interaction.
Zhengui Huang, Nanjing University of Science and Technology
Dr Zhengui Huang obtained his PhD (Engineering Mechanics) from the Key Laboratory of Transient Physics, Nanjing University of Science and Technology. Presently he is working as a teacher in the same university. He has published 15 Journals papers and 8 conference papers. His research interests include: CFD, computational fluid dynamics of supersonic flow, external ballistics theory and application and CFD of water entry problem.
Yongjie Gou, Aerospace System Engineering Shanghai
Mr Yongjie Gou obtained his ME (Aircraft Design) from Northwestern Polytechnical University (NPU). He is working in the Shanghai Academy of Spaceflight Technology. He has about 10 journal papers and 8 conference papers to his credit. His research areas includes: CFD, aerodynamics, propulsion.
Qizhong Tang, China North Industries Group Corporation
Mr Qizhong Tang obtained his BE (Mechanical Engineering) from Nanjing University of Science & Technology, China. He is working in the Navigation and Control Technology Institute, China North Industries Group Corporation. His research areas includes: aerodynamics, propulsion and control science and technology.
Zhihua Chen, Nanjing University of Science and Technology
Dr Zhihua Chen received two PhDs; one is from the New Jersey Institute of Technology, USA in 2001, and the other is from Nanjing University of Science & Technology, China, in 1997. Currently working as a professor at the Key Laboratory of Transient Physics at Nanjing University of Science & Technology, Nanjing, China. He has more than 200 papers. His research interests include: supersonic and hypersonic flow, detonation, and flow control.
Published
2018-10-31
How to Cite
Zhu, S., Huang, Z., Gou, Y., Tang, Q., & Chen, Z. (2018). Numerical Investigations on Wedge Control of Separation of a Missile from an Aircraft. Defence Science Journal, 68(6), 583-588. https://doi.org/10.14429/dsj.68.12552
Section
Missile System