Aircraft Steering Vane Control System Asymmetric Rudder Deflection
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Solution Overview
Problem
Conventional electrical control systems for aircraft rudder do not adequately adapt to varying flight conditions, particularly during strong side winds, leading to restricted rudder deflection and reduced control effectiveness.
Innovation Solution
The control system dynamically adjusts the first and second deflection limits of the rudder based on current flight parameters, such as movement phase, speed, Mach number, altitude, sideslip angle, and thrust, allowing for asymmetric variation of these limits to enhance rudder range and effectiveness, especially during rolling and strong side wind conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If fixed symmetric deflection limits are applied to the rudder, then the rudder structure can be simplified and mass reduced, but the control effectiveness is reduced during strong side wind conditions
Solution Approach 1:
The patent implements dynamic adjustment of rudder deflection limits based on real-time flight conditions. The control system continuously monitors parameters such as aircraft speed, altitude, and sideslip angle, and dynamically modifies the deflection limits accordingly. This allows the rudder to operate with optimized deflection ranges that adapt to varying aerodynamic conditions, particularly during strong side wind conditions where enhanced control authority is needed.
Solution Approach 2:
The patent changes the operational parameters of the rudder by adjusting its deflection limits as a function of flight conditions. The system modifies the maximum and minimum deflection angles based on real-time measurement of flight parameters, thereby optimizing the rudder's control effectiveness across different operating regimes while maintaining structural simplicity.
2Device complexity
If fixed deflection limits are used, then the control system is simpler, but the rudder cannot provide adequate control authority during strong side winds when maximum deflection is needed
Solution Approach 1:
The patent implements a feedback control mechanism that continuously monitors flight conditions and adjusts the rudder deflection limits accordingly. Sensors measure parameters such as aircraft speed, altitude, and sideslip angle, and this information is fed back to the control system which then dynamically modifies the deflection limits to ensure adequate control authority is available when needed, particularly during strong side wind conditions.
Solution Approach 2:
The control system transitions from a static, fixed deflection limit configuration to a dynamic system that continuously adapts the deflection limits based on real-time flight conditions. This dynamic adjustment ensures that the rudder maintains optimal control effectiveness across the entire flight envelope while responding appropriately to strong side wind conditions.
3Strength
If the rudder deflection range is limited symmetrically, then the structure can be optimized for standard conditions, but the control effectiveness is reduced during asymmetric flight conditions such as strong side winds
Solution Approach 1:
The patent dynamically changes the rudder deflection parameters based on flight conditions. The system adjusts the maximum and minimum deflection angles asymmetrically when needed, such as during strong side wind conditions, allowing the rudder to provide enhanced control authority in the direction opposing the wind while maintaining structural optimization for standard operating conditions.
Solution Approach 2:
The patent implements a dynamic adaptation mechanism that modifies the rudder's operational characteristics in response to varying flight conditions. The system continuously adjusts the deflection limits to optimize control effectiveness for asymmetric conditions such as strong side winds, while maintaining the structural design optimized for standard conditions.
Data Source
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AI summary
The invention concerns a system (1) comprising a steering vane (2) which can turn within a rudder deflection range which is limited by first and second rudder deflection limits, and means (12) for asymmetrically varying said first and second rudder deflection limits based on the current values of the aircraft flight parameters.