Accession Number:

ADA605302

Title:

Missile Flight Control Using micro-Actuated Flow Effectors - Review of Fiscal Year 2005/2006 Progress

Descriptive Note:

Technical note

Corporate Author:

DEFENCE RESEARCH AND DEVELOPMENT CANADA VALCARTIER (QUEBEC)

Personal Author(s):

Report Date:

2006-08-01

Pagination or Media Count:

156.0

Abstract:

Superior performance is a key goal in weapons design. Missiles must fly faster and farther, and be more agile, compact and lightweight. The United States have been very active in the development of smart structures for military applications such as missile guidance. For example, DARPA and the Air Force Office of Scientific Research are sponsoring the development of miniaturized active flow technologies to achieve far-term objectives for smart bombs and missiles. Their principal concepts for altering the flow around a body are centred on miniaturized devices that are embedded in the missile skin andor airframe. The objective of this project is to demonstrate with hardware and software 1 engineered micro-flow effectors of specific geometry and placement that are able to produce controllable aerodynamic forces on a missile under supersonic conditions or a delta wing under subsonic conditions, 2 microactuators that are able to meet the force, kinematic and thermal requirements set by the aerothermal environment and 3 control algorithms running on non-flightweight electronics and feedback sensors that take in command signals and output appropriate actuator drive signals to produce the desired aerodynamic force on a wind or water tunnel delta wing model. This report documents the progress made by the project members for fiscal year 20052006 in the areas of missile aerodynamics, delta wing aerodynamics, microactuator modeling, control synthesis and micro-fabrication.

Subject Categories:

  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE