Compound Aircraft Asymmetric Wing Flaps Anti-Torque
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Solution Overview
Problem
Rotary wing compound aircraft require significant mechanical power for hovering and takeoff due to the need for both main rotor lift and anti-torque device operation, which increases the power demand and limits aircraft performance.
Innovation Solution
The implementation of movable flaps on the wings, positioned asymmetrically to generate additional torque by creating differential longitudinal aerodynamic forces when subjected to the main rotor's air stream, reducing the mechanical power needed for the anti-torque device and thus the overall power plant demand.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a main anti-torque device is provided to counterbalance rotor torque, then the aircraft achieves balance about the yaw axis and maneuverability, but the mechanical power required from the power plant increases significantly
Solution Approach 1:
The wing-and-flap assembly uses the air stream from the main rotor (which would otherwise be wasted) to generate longitudinal aerodynamic forces that create additional anti-torque. The system serves itself by converting the kinetic energy of the passing air into useful torque without requiring additional mechanical power from the power plant.
Solution Approach 2:
The air stream from the main rotor acts as an intermediary medium. Instead of directly using mechanical power to drive an anti-torque device, the invention uses this air stream to indirectly generate the required torque through asymmetric flap deflection, reducing the direct mechanical power demand.
2Stability of the object's composition
If symmetric flaps are used on both wings, then the aircraft structure remains balanced, but no additional torque is generated to reduce anti-torque device power requirements
Solution Approach 1:
The invention introduces asymmetry in flap deflection angles between the left and right wings. This asymmetric configuration allows the wing-and-flap assembly to generate a net longitudinal aerodynamic force that produces additional torque about the yaw axis, directly reducing the power required by the main anti-torque device while maintaining structural integrity.
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 solution reduces the mechanical power required for anti-torque, allowing for increased payload capacity and improved aircraft performance without increasing weight, complexity, or cost, while maintaining efficient lift reduction.
Implementation Method 1
each flap being oriented asymmetrically relative to the air stream generated in reaction to the aerodynamic lift of the main rotor so that the longitudinal aerodynamic coefficient CT of the aerodynamic profiles are different on either side of the fuselage
Implementation Method 2
The翼- flap assemblies generate longitudinal aerodynamic forces directed in the longitudinal direction X under the effect of the air stream
Data Source
AI summary
A compound aircraft having a fuselage, a main rotor, a main anti-torque device and two wings positioned on either side of the fuselage. Each wing has at least one movable flap situated at its trailing edge. The flaps can be deflected asymmetrically relative to an air stream generated in reaction to the lift of the main rotor on either side of the fuselage so as to create longitudinal aerodynamic forces in opposite directions on either side of the fuselage and consequently create an additional torque that is added to the main torque from the main anti-torque device.