Deployable Aerodynamic Device with Dynamic Coupling to Reduce Actuator Loads
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Solution Overview
Problem
Conventional leading and trailing edge aerodynamic devices require large actuators to overcome aerodynamic forces, leading to increased weight, power consumption, and reduced efficiency in aircraft operations.
Innovation Solution
Deployable aerodynamic devices with a first component pivotably coupled to a lifting body and a second component translatably coupled to the lifting body, where the actuator load is reduced by leveraging external aerodynamic forces, allowing the device to move along a motion path with increasing and then decreasing load requirements, optimizing actuator usage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional actuators are sized to overcome aerodynamic forces during device deployment, then the device can be deployed reliably, but the actuator size and weight increase significantly
Solution Approach 1:
The patent employs a dynamic coupling mechanism where the aerodynamic device is initially pinned to the wing at a first location during deployment, then transferred to a second location after deployment. This dynamic reconfiguration allows the actuator to only overcome aerodynamic forces during the initial deployment phase, rather than continuously, significantly reducing the required actuator size and weight while maintaining reliable deployment.
Solution Approach 2:
The deployment process is segmented into distinct phases: initial deployment with the device pinned at the first location, transition phase where the device is uncoupled and repositioned, and final deployed position. This segmentation allows the actuator to perform different functions at different times, reducing the peak load requirements and enabling smaller, lighter actuators.
2Force
If large actuators are used to deploy aerodynamic devices, then deployment force requirements are met, but power consumption increases significantly
Solution Approach 1:
The dynamic coupling mechanism enables the actuator to provide high force only during the brief initial deployment phase when the device is pinned at the first location. Once deployed, the device is uncoupled and repositioned using minimal force. This dynamic operation pattern significantly reduces average power consumption compared to conventional actuators that must continuously overcome aerodynamic forces.
Solution Approach 2:
The deployment process uses periodic action with distinct high-force and low-force phases. The actuator delivers high force during initial deployment, then transitions to low-force operation during the transition and stowed phases. This periodic force application pattern reduces overall energy consumption while maintaining adequate deployment force when needed.
3Adaptability or versatility
If conventional aerodynamic devices are used, then flight control functions are achieved, but integration difficulty increases due to large actuator size
Solution Approach 1:
The dynamic coupling mechanism with its two-location pinning system enables compact actuator design, which simplifies integration into aircraft structures. The actuator can be smaller and lighter while still achieving the required flight control functions, making it easier to integrate into existing aircraft designs without requiring large structural modifications.
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
The solution reduces the size and power requirements of actuators, facilitating easier integration and reducing overall aircraft weight, while enhancing operational efficiency by minimizing actuator load throughout the deployment process.
Implementation Method 1
the aerodynamic forces acting on the deployable device to reduce the load required by the actuator device to deploy the deployable device
Data Source
AI summary
Deployable aerodynamic devices with reduced actuator loads, and related systems and methods are disclosed. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.