Design and Research of Wind Tunnel Test for Deflectable Nose

Abstract:

A wind tunnel test is designed to study aerodynamic effects of one individual rocket with deflectable nose. The test measures pressure with U-bend tube which is cost effective. Using rubber tubes in different lengths to measure pressure distributions of a flat-plate, and calculating how rubber tube affects the measurement, in order to modify the measured surface pressure of the nose. The surface pressure varies on different points while yawing angle and attack angle changes, the changing regularity could provide data for following numerical simulation and trajectory control.

• Periodical: Applied Mechanics and Materials (Volumes 423-426)
• Pages: 2063-2067
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.423-426.2063
• Online since: September 2013
• Authors: Bo Zhang, Shu Shan Wang, Meng Yu Cao, Yu Xin Xu
• Keywords: Aerodynamic Effect, Deflectable Nose, Wind Tunnel

References

[1] Landers M G, Hall L H. Deflectable nose and canard-controls for a fin-stabilized projectile at super-sonic and hypersonic speeds. AIAA-2003-3805, (2003).

DOI: 10.2514/6.2003-3805

[2] Meurnier M. Viscous CFD analysis of a deflected nose axisymmetric projectile at high speeds. Cranfield: Cranfield University, (2005).

[3] Shoesmith B, Birch T. CFD Analysis of a supersonic projectile with deflectable nose control. AIAA-2006-3200, (2006).

DOI: 10.2514/6.2006-3200

[4] Hathaway W, Winchenbach G, Krieger J. Free-flighttests of 10-degree cones with a one degree articulation angle. AIAA-1999-0434, (1999).

DOI: 10.2514/6.1999-434

[5] Wayne V S, Robert J A, Williams D P. Articulated nosemissile control actuation system: United States, 6364248B1. 2002-04-02.

[6] Berry R P, Lawless D F, Cayson S C, et al. Magnetostrictive missile guidance system: United States, 6467722. 2002-10-02.

[7] Landers M G，Hall L H．Deflectable Nose and Canard-Controls for a Fin-Stabilized Projectile at Super-Sonic and Hyper SonicSpeeds．AIAA-2003-3805.

[8] Shoesmith B，Birch T．CFD Analysis of a Supersonic Projectile with Deflectable Nose Control. AIAA-2006-3200.

DOI: 10.2514/6.2006-3200

[9] Fan Jiechuan, Yu Tao. Low speed pressurized wind tunnel at home which is building. Journal of Experiments in Fluid Mechanics, Vol. 19(2005) , pp.1-6.

[10] LI Yan, Deng Xueying, WangYankui. Application of Static Pressure Measurement System in Wind Tunnel Test. Ordnance Industry Automation, Vol. 29 (2010), pp.81-84.

[11] Wang Xunnian. Low Speed Wind Tunnel Experiment. BeiJing：National Defence Industry Press , (2002).

[12] Chen Mo, Ma Handong. Aerodynamic Experiments in Large-Size Wind Tunnel Can be Realized in Common Small-Size Wind Tunnel，Journal of Astronautics, Vol. 26(2005) , pp.131-136.

[13] Zhang Wei. etc. Design and error analysis on pressure measurement system of low speed pressurized wind tunnel, Journal of Experiments in Fluid Mechanics, Vol. 23(2009) , pp.95-103.

[14] Qian Xingfang, Lin Ruixiong, Zhao Yanan. Flight Mechanics of Guided missile. Beijing: Beijing Institute of Technology Press, (2011).