Wind Tunnel Tests on a Tube-Launched Missile Configuration with a Deflectable Nose Control and a Novel Wrap-Around Fin Stabiliser

摘要

Experiments were conducted in the Mach number range 0.80 to 2.00 on a tube-launched missile configuration with a deflectable nose control and a wrap-around fin stabiliser having six fins disposed in a symmetrical triform arrangement. The results show that the control effectiveness increases markedly with Mach number. Trim curves are non-linear at subsonic speeds and approach linearity at supersonic Mach numbers. The results were applied to a small hypothetical missile configuration and indicate that the nose control is powerful enough to provide a terminal control capability. For the case considered, in subsonic flight the missile must fly on a near-ballistic trajectory. However, in supersonic flight the control is powerful enough to permit horizontal flight above M = 1.5 while retaining a sufficient reserve to provide a terminal correction capability. Detailed control system assessments were not made. (Author)