Accession Number:

ADA142082

Title:

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

Descriptive Note:

Technical rept

Corporate Author:

WEAPONS SYSTEMS RESEARCH LAB ADELAIDE (AUSTRALIA)

Personal Author(s):

• Thomson, K. D.

Report Date:

1983-08-01

Pagination or Media Count:

36.0

Abstract:

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.

Descriptors:

• *DEFLECTION
• *CONFIGURATIONS
• *WIND TUNNEL TESTS
• *CONTROL SURFACES
• *NOSE CONES
• CONTROL
• FLIGHT
• SUBSONIC FLIGHT
• TUBE LAUNCHED
• STABILIZATION SYSTEMS
• GUIDED MISSILE MODELS
• SUPERSONIC FLIGHT
• HORIZONTAL ORIENTATION
• MACH NUMBER
• AUSTRALIA
• FINS

Subject Categories:

• Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE