device for recent uninhabited air vehicle (UAV) and flying automobile developments because of their compact structure and high lifting performance. The proposed research is dedicated to developing a high fidelity and efficient ducted fan modeling and simulation tool for helicopter anti-torque and UAV lifting applications. The development will focus on the following:
(1) The development of an efficient blade element fan model that can be applied for ducted fan performance, stability, and control analysis and simulation.
(2) The development of duct aerodynamic models with selective fidelity to address the duct lift augmentation effect and duct drag and moment variations in both axial and cross-wind conditions.
(3) The development of a coupled duct-fan model that allows for mutual aerodynamic interaction of the duct and the fan. Efforts will also be made to develop an effective and efficient rotor/airframe/duct/fan aerodynamic interaction model. The model will provide a comprehensive modeling tool to support the simulation of rotorcraft and VTOL air vehicles equipped with ducted fan devices.
Project 12: OH-58D Model for Flight School XXI
Summary of Services Performed: Integration and Testing of OH-58D flight dynamics model with the simulator for U.S. Army Flight School XXI
Under a contract ART has provided a flight dynamics model of the OH-58D helicopter and assisted in its integration and acceptance testing with two Operational Flight Trainers. The flight dynamics model was developed using ART’s FLIGHTLAB Development System, a computer aided engineering tool for flight dynamics modeling and analysis. The trainers were tested to FAA Level D certification standards. This effort involved the integration of the flight dynamics software the cockpit, motion platform, visual display system, control loaders and Instructor Operator Station (IOS). The response of the flight dynamics model was compared to experimental flight test data for a wide range of flight conditions and maneuvers and the model was tuned to satisfy the tolerances required by the acceptance testing. The quantitative comparison between simulator and flight test data was automated to allow for field monitoring of the simulator readiness. Simulator hardware was also included in the automated quantitative testing. Over 50 malfunctions were implemented and tested. Qualitative testing was performed by experienced OH-58D pilots flying the simulator through the training tasks currently being trained in the actual aircraft. The simulators have now been delivered to Ft. Rucker, AL and are being used in the Army’s Flight School XXI program.
Project 13: Sling Load Modeling for Handling Qualities Analysis
Summary of Services Performed: Modeling and validation of sling loads for handling qualities analysis
Slung load handling is a unique capability of rotorcraft widely applied in support of cargo transportation, rescue, and the special construction in areas where no other air or ground vehicles can operate. The presence of a sling load can degrade rotorcraft handling qualities and reduce the flight envelope. This project has successfully developed a multi-body and unsteady rotorcraft/sling load modeling and simulation tool in FLIGHTLAB for an accurate assessment of the sling load dynamic stability and the operational envelope. The sling load modeling tool developed can simulate arbitrary sling load configuration under influence of unsteady sling load airloads.
Advanced Rotorcraft Technology, Inc.