NASA STTR 2011 Solicitation


PROPOSAL NUMBER: 11-1 T2.02-9949
RESEARCH SUBTOPIC TITLE: Aeroservoelastic (ASE) Control, Modeling, Simulation, and Optimization
PROPOSAL TITLE: Vorticity State Estimation For Aeroelastic Control

NAME: Tao of Systems Integration, Inc. NAME: California Institute of Technology
STREET: 144 Research Drive STREET: 1200 E. California Blvd., Mail Code 201-15
CITY: Hampton CITY: Pasadena
STATE/ZIP: VA  23666 - 1339 STATE/ZIP: CA  91125 - 0001
PHONE: (757) 220-5040 PHONE: (626) 395-6357

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Arun Mangalam
144 Research Drive
Hampton, VA 23666 - 1339
(757) 220-5040

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 1
End: 3

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
Flight control, structural reliability, and efficiency depend critically on the ability to assess the time-accurate unsteady aerodynamic loads and moments for each lifting surface under nominal and adverse flow conditions. Tao Systems and California Institute of Technology propose to develop a flow control system that utilizes advanced sensors and a vorticity state estimator (VSE) to reach flow states unattainable without continuous control feedback. The flow control scheme enables manipulation of the vorticity state to achieve performance objectives, such as short take-off/landing through controlled aerodynamic lift at angles of attack near stall.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Vorticity-based flow control system will enable a number of revolutionary capabilities across a wide speed range, including, but not limited to: (1) shorter take-off and landing, (2) safe, reliable aircraft operation in turbulent condition, and (3) larger passenger and cargo capacity. The primary difficulty in all three revolutionary capabilities is the uncertainty in aerodynamic load & moments generated by the airstream in design and off-design conditions, e.g., turbulent flows, high angles of attack and unsteady flows. Measuring the unsteady aerodynamic loads/moments through the vorticity state reduces the aerodynamic uncertainty enabling the aircraft to timely, robustly compensate for the adverse, unsteady flow conditions. Therefore, the proposed innovation could be of significant interest to the aircraft civilian industry.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
For national security, the ability to cruise efficiently at a range of altitude, enabled by a substantial increase in cruise lift-to-drag (L/D) ratios over today's high-altitude reconnaissance aircraft, is vital, providing sustained presence and long range. Vorticity-based flow control would enable the efficient, robust active control of adaptive, lightweight wings to optimize lift distribution to maximize L/D. Cost-effectively improving the energy capture and reliability of wind turbines would help national renewable energy initiatives. A vorticity state estimator could provide output for control feedback to mitigate the turbine blade lifetime-limiting time varying loads generated by the ambient wind.

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Air Transportation & Safety
Algorithms/Control Software & Systems (see also Autonomous Systems)
Attitude Determination & Control
Autonomous Control (see also Control & Monitoring)
Avionics (see also Control and Monitoring)
Condition Monitoring (see also Sensors)
Health Monitoring & Sensing (see also Sensors)
Inertial (see also Sensors)
Models & Simulations (see also Testing & Evaluation)
Navigation & Guidance
Positioning (Attitude Determination, Location X-Y-Z)
Recovery (see also Autonomous Systems)
Recovery (see also Vehicle Health Management)

Form Generated on 11-22-11 13:44