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HELICOPTERS
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keywords:(HELICOPTERS)
Evaluation of Mean Loading Effects on Vibration-Based Active Airframe Damage Detection
Spanwise Differences in Static and Dynamic Stall on a Pitching Rotor Blade Tip Model
Evaluation of Visual Augmentation Methods for Rotorcraft Pilots in Degraded Visual Environments
An Assessment of RCAS Performance Prediction for Conventional and Advanced Rotor Configurations
Maneuverability Assessment of a Compound Helicopter Configuration
Rotor Vortex Wake in Close Proximity of Walls in Hover
Performance and Loads Predictions of a Mach-Scaled Rotor at High Advance Ratios
Simulation Testing of Advanced Response Types for Ship-Based Rotorcraft
Parametric Instability of Face-Gear Drives due to Meshing Loads
Variable rotor speed control for an integrated helicopter/engine system
Physics-Based Modeling of Viscous Ground Effect for Rotorcraft Applications
An Experimental Investigation of Ground Effect on a Quad Tilt Rotor in Hover
A Semiempirical Noise Modeling Method for Helicopter Maneuvering Flight Operations
New Methods to Subjectively and Objectively Evaluate Adverse Pilot Couplings
Aeroelastic Analysis of Avian-Based Flexible Flapping Wings for Micro Air Vehicles
Experimental Analysis of the Aerodynamics of Long-Shrouded Contrarotating Rotor in Hover
Helicopter Slung Load Control Using Lagged Cable Angle Feedback
Prediction of Rotorcraft Design Impacts on Maneuverability Characteristics
A Real-Time Expert Control System For Helicopter Autorotation
Characterization of CH-47D Rotor System Fault Signatures Using a Comprehensive Model
Development of a Quad Cycloidal-Rotor Unmanned Aerial Vehicle
Advanced Composite Materials Technology for Rotorcraft through the Use of Nanoadditives
Optimum Loading and Induced Swirl Effects in Hover
Modular Multisolver Approach for Efficient High-Fidelity Simulation of the HART II Rotor
Eigenstructure Control: A Rotorcraft Handling Qualities Engineering Tool
Performance Enhancement in Dynamic Stall Condition Using Active Camber Deformation
Dynamic Stall Life Cycle on a Rotating Blade in Steady Forward Flight