Affiliation:
1. Beijing Institute of Technology
2. AVIC Keeven
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.
Publisher
Trans Tech Publications, Ltd.
Reference14 articles.
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).
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).
4. Hathaway W, Winchenbach G, Krieger J. Free-flighttests of 10-degree cones with a one degree articulation angle. AIAA-1999-0434, (1999).
5. Wayne V S, Robert J A, Williams D P. Articulated nosemissile control actuation system: United States, 6364248B1. 2002-04-02.