|
Innovative Methods for Modeling and Simulation of Tiltrotor Aircraft
Navy SBIR 2008.1 - Topic N08-013 NAVAIR - Mrs. Janet McGovern - [email protected] Opens: December 10, 2007 - Closes: January 9, 2008 N08-013 TITLE: Innovative Methods for Modeling and Simulation of Tiltrotor Aircraft TECHNOLOGY AREAS: Air Platform, Information Systems, Human Systems ACQUISITION PROGRAM: PMA-275 - V-22 Program, ACAT I OBJECTIVE: Develop innovative aerodynamic modeling and simulation approaches for rotary wing and tiltrotor aircraft that provides an efficient means of easily updating new and existing simulation math models in order to increase model fidelity and reduce update time. DESCRIPTION: During aircraft development and testing, the aerodynamic, six degree of freedom simulation math models are continuously adjusted to improve correlation with wind tunnel and flight test data in order to accurately predict and depict aircraft response to varying degrees of success. However, as with all simulations, model complexity and design currently limit our ability to efficiently update the math model. Systemic problems arise from bookkeeping of model correlation adjustments in incorrect or physically improbable locations due to the complexity of the update cycle. Most current rotorcraft/tiltrotor simulation models are cumbersome and onerous to update. Large quantities of manpower and time are required to correlate and update the model with flight and wind tunnel data. Without high fidelity modeling and simulation tools that allow for efficient methodologies for model updating, the aircraft flight test and training are at a higher risk. An innovative real-time modeling capability is needed, that can be easily updated with flight test and wind tunnel data, to accurately predict aircraft characteristics. By reducing the time and complexity associated with updating the math model, the fidelity of the model should increase as more data can be incorporated into the model. Having a higher fidelity simulation math model would allow for more succinct flight test planning and execution (less flights, less money, more predictive capability), allow for better trainers to be used for training and tactics, techniques, and procedures development; allow for better training to reduce mishap potential; and ultimately allow for more accurate mishap investigation assistance. While current simulations employ an open architecture design which allows for addition of new modules and capabilities, these do not allow for quick, easy, and accurate simulation update/refinement of the model based on new data. Methods for automated simulation update based on wind tunnel and flight data have been recently employed for fixed wing platforms (Ref 4 and 5); however, as of yet, these methods have not been utilized for rotary platforms due to the increased complexity involved with the inclusion of a rotor. For rotary wing platforms, past experience has shown that component based modeling is required for improved predictive capability. Updating a component based model, however, is time consuming and difficult. Non-component based simulations, while easier to update and validate, are not suited for predictive analysis. PHASE I: Develop an innovative approach for the aerodynamic modeling and simulation of rotary wing and tiltrotor aircraft that provides the capability for efficiently updating new and existing math models with flight test and wind tunnel data while still increasing model fidelity and predictive capability. Demonstrate the feasibility if the approach through simple modeling examples that demonstrate the ability to perform updates. PHASE II: Fully develop the approach into a prototype modeling tool. Demonstrate the capability of the tool by performing a simulation on a military tiltrotor or rotorcraft as the case study, and verify the ability to update the model with a limited set of flight test and/or wind tunnel data to improve model fidelity. PHASE III: Develop a real time, production ready, rotorcraft/tiltrotor simulation tool. Perform verification and validation of the developed technology and demonstrate that the new tool can be easily updated with a wide set of flight test and wind tunnel data and that the model accurately predicts aircraft characteristics. Transition the new capability to tiltrotor and rotorcraft platforms. PRIVATE SECTOR COMMERCIAL POTENTIAL/DUAL-USE APPLICATIONS: The model architecture developed here can be applied to helicopter and tiltrotor platforms via model tailoring. The basic architecture and model methodology can be consistent. Model incorporation in other platforms can result in a potential reduction in development and operation costs. REFERENCES: Available on the NASA Technical Report Server or from NASA directly: 2. Ferguson, Samuel W. "A Mathematical Model for Real Time Flight Simulation of a Generic Tilt-Proprotor Aircraft". NASA-CR-166536. Systems Technology, Inc. Mountain View, CA. October, 1983. 3. Harendra, P. B., M. J. Joglekar, T. M. Gaffey, R. L. Marr. "V/STOL Tilt Rotor Study � Volume V: A Mathematical Model for Real Time Flight Simulation of the Bell Model 301 Tilt Rotor Research Aircraft". NASA-CR-114614, 13 April 1973 4. Klein, Vladislav, Eugene A. Morelli. "Aircraft System Identification � Theory and Practice". AIAA Education Series, Reston Virginia. 2006. 5. Morelli, E., D. Ward. "Automated Simulation Updates based on Flight Data". AIAA 2007-6714. Presented at the AIAA Atmospheric Flight Mechanics Conference in Hilton Head, South Carolina. 20-23 August 2007.3w www.aiaa.org KEYWORDS: Modeling; Simulation; Tiltrotor; Helicopter; Aerodynamic; Aircraft TPOC: (301) 342-8546
|