Control Vane Orientation for Ducted-Rotor Yaw Stability
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Solution Overview
Problem
Ducted-rotor aircraft face challenges in yaw control, particularly in windy conditions, due to wind forces generated by stabilizer, ducted rotor, and fuselage surfaces, which affect directional stability and control.
Innovation Solution
The orientation of control vanes attached to the ducted rotors is optimized to maximize moment arms, allowing for effective yaw control by positioning them to align with the nominal yaw axis and center of gravity, enabling efficient directional movement in both helicopter and airplane modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If control vanes are positioned to maximize moment arms for yaw control, then directional stability and control effectiveness are improved, but the aircraft becomes more sensitive to wind forces generated by stabilizer, ducted rotor, and fuselage surfaces
Solution Approach 1:
The patent optimizes the orientation angles of control vanes relative to the rotor disk plane and adjusts vane area distributions to maximize moment arms for yaw control. By changing geometric parameters of the control surface configuration, the system achieves improved directional control effectiveness while accounting for wind force interactions
Solution Approach 2:
The patent acknowledges that wind forces generated by stabilizer, ducted rotor, and fuselage surfaces create sensitivity issues, but converts this challenge into a benefit by optimizing control vane orientations to leverage these wind forces for enhanced yaw control effectiveness, particularly in windy operating conditions
2Measurement precision
If control vanes are oriented to align with nominal yaw axis and center of gravity, then yaw control precision is improved, but device complexity increases due to precise positioning requirements
Solution Approach 1:
The patent applies different orientation angles and positioning configurations to specific control vanes based on their local requirements for maximizing moment arms. Each control surface is locally optimized for its specific position on the aircraft, allowing precise yaw control without requiring uniform complex positioning systems across all components
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This configuration enhances yaw control and stability, particularly during hovering in helicopter mode and forward flight in airplane mode, by optimizing the moment arms generated by control surfaces, improving the aircraft's ability to navigate various flight conditions.
Implementation Method 1
control vanes attached to the ducted rotors is optimized to maximize moment arms, allowing for effective yaw control
Data Source
AI summary
A ducted-rotor aircraft may include a fuselage and first and second ducts that are coupled to the fuselage at respective first and second locations. The first location may be on a first side of a fuselage of the aircraft and spaced from a nominal yaw axis of the aircraft. The second location may be on an opposed second side of the fuselage and spaced from the nominal yaw axis. Each duct may include a rotor that is disposed in an opening that extends through the duct. Each rotor may include a plurality of blades. Each duct may further include a control vane that is mounted aft of the plurality of blades and that is pivotable about a vane axis that is oriented toward the nominal yaw axis.