ACTUATOR INTEGRATED MISSILE STEERING SYSTEM (AIMSS) FOR SUPERSONIC MISSILES

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$749,999.00
Award Year:
2008
Program:
SBIR
Phase:
Phase II
Contract:
N00014-08-C-0674
Award Id:
82737
Agency Tracking Number:
N071-095-1014
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
4415 Euclid Avenue, Suite 500, Cleveland, OH, 44103
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
557510336
Principal Investigator:
Mehul Patel
Director, Aerodynamics Gr
(216) 649-0399
patel@orbitalresearch.com
Business Contact:
Joseph Snyder
Vice President
(216) 649-0399
snyder@orbitalresearch.com
Research Institute:
n/a
Abstract
Alternative flight control methods that can reduce or eliminate the need for movable fins or wings while maintaining or improving the aerodynamic control performance of supersonic cruise missiles are sought. Orbital Research Inc, in collaboration with the University of Toledo, proposes to continue the development of an innovative Actuator Integrated Missile Steering System (AIMSS) for aerodynamic control of subsonic-to-hypersonic cruise missiles using active flow control and micro-actuator technologies. The AIMSS will utilize small, deployable and/or activatable devices with innovative flow control techniques to provide controls for missile maneuvering and trimming. The main objectives of the proposed system are to: (a) provide and maintain sustainable control authority over a wide range of flow speeds from subsonic to supersonic flows (Mach 0.1 to 4), (b) reduce the design complexity, weight, drag, cost and power requirements of the conventional control actuation subsystems through efficient employment of microactuators and advanced control approaches, and (c) reduce or eliminate the need for movable fins or wings on supersonic cruise missiles which will also allow the system to be integrated into and launched from various platforms. Other potential benefits of the AIMSS include increased range, payload capacity, aero-structural efficiency and endgame maneuvering.

* information listed above is at the time of submission.

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