Aircraft Wing Control System Torque Balancing
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Solution Overview
Problem
Aircraft wing twisting due to dynamic air pressure on ailerons during flight can lead to aileron reversal, where control inputs result in unintended effects, posing a challenge in maintaining stable flight.
Innovation Solution
A wing control system with a shaft and actuation means that applies a variable torque, utilizing outboard and inboard moment transfer mechanisms to balance the torque and counter twisting, with adjustable moment ratios to optimize the system for specific aircraft types.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If an aileron is pivoted during forward motion of the aircraft, then the aileron control input produces the intended effect, but dynamic air pressure induces wing twisting that may cause aileron reversal
Solution Approach 1:
The system applies a counter-moment to the wing through the planetary gearbox before the dynamic air pressure can cause excessive twisting. The inboard moment transfer means generates an opposing moment that preemptively counteracts the aerodynamic forces that would otherwise cause aileron reversal, allowing the aileron to maintain its intended control effect throughout the full range of motion.
Solution Approach 2:
The planetary gearbox acts as an intermediary mechanism between the aileron control system and the wing structure. It transfers and modulates the control moments, distributing them between the aileron (outboard moment) and the wing (inboard moment), thereby mediating the interaction between control inputs and wing twisting while maintaining control effectiveness.
2Strength
If a rigid connection is used between the aileron control system and the wing, then structural strength is improved, but wing twisting due to dynamic air pressure cannot be counteracted
Solution Approach 1:
The connection between the control system and the wing is segmented into multiple functional components: the planetary gearbox with separate sun gear (connected to aileron) and ring gear (connected to wing), and the inboard moment transfer means. This segmentation allows independent optimization of structural strength and control effectiveness, as each component can be designed to handle specific loads and moments without compromising the other.
Solution Approach 2:
The system transitions from a static rigid connection to a dynamic moment-transfer system. The planetary gearbox and inboard moment transfer means actively modulate the moments between the control system and the wing based on flight conditions, allowing the structure to maintain strength while dynamically adjusting to counteract twisting forces during aileron operation.
3Device complexity
If the moment transfer ratio is fixed, then the system design is simplified, but the system cannot be optimized for different aircraft types and operating conditions
Solution Approach 1:
The moment transfer ratio is made variable through the adjustable inboard moment transfer means, allowing the system to adapt to different aircraft types and operating conditions. The adjustability enables optimization of the moment distribution between the aileron and the wing for various flight regimes and aircraft configurations, enhancing versatility without requiring complete redesign for each application.
Solution Approach 2:
The system allows change in the moment transfer parameter (the ratio of inboard to outboard moments) to optimize performance for different aircraft types. By adjusting this parameter, the same basic system architecture can be tailored to specific aircraft characteristics, weight distributions, and aerodynamic properties, providing adaptability across diverse applications.
Data Source
AI summary
The invention provides a wing control system aimed at countering the aeroelastic effect of twisting of a length of wing of an aircraft due to dynamic air pressure acting on an aileron of the wing. The wing control system includes a shaft extending along the length of wing and actuation means responsive to aileron control inputs to induce a variable torque T in the shaft. Outboard of the length of wing, the system operatively transfers T partially to the aileron to pivot the aileron and partially to the wing at an outboard end of the length of wing to counter twisting of the length of wing due to dynamic air pressure on the aileron. Inboard of the length of wing, the system operatively transfers T to the aircraft, e.g. to its fuselage, thereby effectively balancing the sum of the moments transferred respectively to the aileron and the wing.