Aircraft Wing Leading Edge Spoiler for Load Alleviation
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Solution Overview
Problem
Existing aircraft wing designs lack an efficient mechanism to dynamically adjust lift generation in response to varying flight conditions, such as high g maneuvers or gusts, which can lead to increased aerodynamic loads.
Innovation Solution
The integration of a leading-edge spoiler device on the aircraft wing, which is rotatably mounted by a hinge and can move between a retracted and a deployed position, allowing lift to be dynamically adjusted based on the center of pressure's moment about the hinge.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a leading-edge spoiler device is added to dynamically adjust lift, then aerodynamic load alleviation during high g maneuvers is improved, but device complexity increases
Solution Approach 1:
The spoiler device is made movable between a retracted position (flush with the upper aerodynamic surface) and a deployed position (rotated at an angle), allowing dynamic adjustment of lift based on flight conditions. The hinge mechanism enables this dynamic reconfiguration to alleviate aerodynamic loads during high g maneuvers or gusts.
Solution Approach 2:
The spoiler device is designed to be actuated by aerodynamic forces itself. When the center of pressure moves forward of the hinge during high load conditions, it automatically generates a moment that rotates the spoiler to the deployed position without requiring external actuation systems.
2Adaptability or versatility
If the spoiler device is made movable between retracted and deployed positions, then adaptability to varying flight conditions is improved, but ease of operation deteriorates
Solution Approach 1:
The spoiler device automatically responds to flight conditions through aerodynamic actuation. The center of pressure movement during varying flight conditions (high g maneuvers, gusts, or normal flight) automatically generates the necessary moments to rotate the spoiler between positions without pilot intervention or complex control systems.
Solution Approach 2:
The device utilizes changes in aerodynamic parameters (center of pressure location) to automatically transition between operational states. As the center of pressure moves forward or aft relative to the hinge during different flight conditions, the spoiler passively adjusts its position accordingly.
3Productivity
If the spoiler surface forms a continuous surface with the upper aerodynamic surface in retracted position, then lift generation efficiency is improved, but the ability to spoil lift when needed deteriorates
Solution Approach 1:
The spoiler surface transitions from a continuous configuration with the upper aerodynamic surface in the retracted position (maximizing lift generation) to a rotated configuration in the deployed position (spoiling lift). This dynamic reconfiguration allows the wing to optimize lift during normal flight and reduce it during high load conditions.
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 effectively reduces lift and alleviates aerodynamic loads during high g maneuvers or gusts, while maintaining efficient lift generation during normal flight conditions, thereby enhancing the wing's operational safety and efficiency.
Implementation Method 1
the spoiler device is rotatably mounted relative to the fixed wing portion adjacent the wing leading edge by a hinge
Implementation Method 2
a center of pressure of the local wing section acts on the spoiler surface to provide a moment about the hinge
Data Source
AI summary
An aircraft wing has a leading edge, a fixed wing portion and a leading-edge spoiler device. The spoiler device is hingedly mounted relative to the fixed wing portion adjacent the leading edge, moveable between retracted and deployed positions. In the retracted position a spoiler surface forms a continuous surface with a fixed wing portion upper aerodynamic surface, and in the deployed position the spoiler surface is rotated relative to the upper aerodynamic surface. In the retracted position the spoiler surface has a first portion forward of the hinge and a second portion aft of the hinge. A center of pressure of the local wing section acts on the spoiler surface providing a moment about the hinge in a first direction to bias the spoiler device to the retracted position and providing a moment about the hinge in a second, opposite direction, rotating the spoiler device to the deployed position.