Active Wingtip Support Using Inertial Load Counteraction
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Solution Overview
Problem
Current aircraft systems face challenges in effectively reducing dynamic loads, such as those caused by gusts, which can lead to increased wing bending moments and structural stress, particularly in existing wing structures that are not designed to accommodate heavy masses like wing tip fuel tanks.
Innovation Solution
An active support system with an actuator and controller is used to move a body, such as a wing tip fuel tank, rapidly across at least one degree of freedom in less than 3 seconds, generating an inertial force equal to or greater than the aerodynamic force, thereby counteracting dynamic loads and reducing structural stress on the aircraft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If a heavy mass like a wing tip fuel tank is mounted on the existing wing structure, then the aircraft can carry more fuel and extend operational range, but the wing bending moment and structural stress increase beyond design limits
Solution Approach 1:
The patent applies counterweight by using an active support system with an actuator to generate inertial forces that counteract the aerodynamic loads on the wing. The movable mass (body) is rapidly displaced to create inertial forces equal to or greater than the aerodynamic forces, thereby reducing the net load on the wing structure and enabling heavy fuel tanks without structural modification
Solution Approach 2:
The patent transforms the static wing structure problem into a dynamic solution by introducing an active support system that rapidly moves a body (with mass) to generate time-varying inertial forces. The actuator moves the body across its entire range of movement in less than 3 seconds, creating dynamic inertial forces that actively counteract the aerodynamic loads during flight, allowing the wing to operate within its structural limits despite carrying heavy fuel tanks
2Strength
If fast-acting movable flight control surfaces are used to redistribute aerodynamic loads, then wing bending moment can be reduced, but the system complexity and response time to dynamic loads increase
Solution Approach 1:
The patent introduces an intermediary element - a movable body (such as a fuel tank or payload) mounted on an active support system - that acts as a mediator between the aerodynamic loads and the wing structure. This intermediary body generates inertial forces that directly counteract the aerodynamic loads, providing a simpler alternative to complex flight control surface systems while achieving the same load reduction effect
3Reliability
If the actuator moves the body rapidly to generate sufficient inertial force, then the dynamic response effectiveness increases, but the energy consumption and mechanical stress on the actuator increase
Solution Approach 1:
The patent employs periodic action by rapidly oscillating the movable body back and forth within its range of movement. The actuator moves the body across the entire range in less than 3 seconds and generates inertial forces that counteract aerodynamic loads. This periodic motion allows the system to continuously generate counteracting forces during dynamic events like gust encounters, maintaining reliability while managing energy consumption through controlled oscillation rather than continuous high-energy operation
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 allows for the reduction of loads on the aircraft structure during dynamic events, enabling the use of heavy masses like wing tip fuel tanks without modifying the existing wing structure, while also providing flexibility in wing tip device design and reducing external loads on passenger cabins.
Implementation Method 1
the actuator is configured to move the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body
Data Source
AI summary
An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.