Aircraft Wing Tip Camber Actuation for Torque Reduction
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Solution Overview
Problem
Aircraft wing tip devices require significant actuator force to return to flight configuration from load-alleviating configuration during flight, which is often beyond the capacity of actuators sized for ground movements, leading to weight penalties in wing design due to oversized actuators.
Innovation Solution
The aircraft wing tip part is designed to pivot between a load-alleviating and flight configuration, with a controllable shape switchable between positive and negative camber using a temperature-responsive deformable component, allowing aerodynamic forces to assist in returning to the flight configuration, reducing the required actuator torque.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If the actuator is sized to move the tip part from load-alleviating to flight configuration during flight, then the required torque increases, but the actuator weight and wing weight increase significantly
Solution Approach 1:
The patent changes the aerodynamic parameters of the tip part by switching between positive camber (cruise shape) and negative camber (recovery shape) configurations. This parameter change allows the aerodynamic forces to provide the necessary torque to move the tip part from load-alleviating to flight configuration, eliminating the need for oversized actuators during flight operations.
Solution Approach 2:
The patent introduces aerodynamic forces as an intermediary mechanism to assist the actuator in moving the tip part. By using the airflow over the wing to generate aerodynamic torque through camber changes, the system reduces the direct mechanical torque requirement on the actuator, thereby reducing actuator size and weight.
2Weight of moving object
If the actuator is sized for ground movements only, then the actuator weight is reduced, but it cannot provide sufficient torque for flight configuration recovery
Solution Approach 1:
The patent modifies the aerodynamic parameters (camber) of the tip part to create a situation where aerodynamic forces naturally assist in returning the wing to flight configuration. This allows a lightweight actuator designed for ground operations to be augmented by aerodynamic forces during flight, ensuring reliable configuration recovery without requiring a heavy-duty actuator.
Solution Approach 2:
The patent uses aerodynamic forces generated by negative camber configuration as a counterbalancing mechanism to offset the weight and torque limitations of a small actuator. The aerodynamic torque acts in opposition to the gravitational and inertial forces that would otherwise prevent a lightweight actuator from recovering the flight configuration.
3Use of energy by moving object
If the tip part maintains positive camber during recovery, then the aerodynamic efficiency is maintained, but the actuator must overcome full aerodynamic resistance
Solution Approach 1:
The patent implements a dynamic system where the tip part's camber configuration can change between positive (cruise) and negative (recovery) states. This dynamic reconfiguration allows the system to optimize aerodynamic efficiency during normal flight while creating favorable aerodynamic conditions during recovery operations, reducing the force requirement on the actuator.
Solution Approach 2:
The patent applies preliminary anti-action by switching to negative camber configuration before or during the recovery process. This creates aerodynamic forces that oppose the resistance that would otherwise be generated by positive camber, thereby reducing the actuator force requirement while preparing the system for efficient recovery.
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 design reduces the force needed to return the wing tip to the flight configuration during flight, enabling a lighter wing design by leveraging aerodynamic forces and minimizing the size and weight of actuators.
Implementation Method 1
a controllable shape switchable between positive and negative camber using a temperature-responsive deformable component
Implementation Method 2
the heater comprises an electrical heating element configured to receive control signals from a remote controller
Implementation Method 3
allowing aerodynamic forces to assist in returning to the flight configuration
Data Source
AI summary
An aircraft wing having a fixed root part hingedly connected to a moveable tip part is disclosed. The tip part is configured to pivot relative to the root part about a substantially horizontal axis, between a load-alleviating configuration in which the tip part is oriented relative to the root part such that at least one of the upper and lower surface of the tip part is positioned away from the respective surface of the root part and a flight configuration in which the upper and lower surfaces of the tip part are continuations of the upper and lower surfaces of the root part. The shape of the tip part is controllably switchable between a cruise shape in which the tip part has positive camber and a recovery shape in which the tip part has negative camber.