Aircraft Wing-Like Element Torque Control for Load Alleviation
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Solution Overview
Problem
The integration of large wing tip devices on aircraft increases structural loads, particularly at the wing root, due to reduced effective lever arm and limited planar areas, which complicates the integration of control surfaces and affects aerodynamic performance.
Innovation Solution
Aircraft equipped with a passive torque control device featuring a rotatable interface that supports the wing root of an additional wing-like element, allowing rotation in airflow to manage torque and reduce loads, utilizing a spring-based system for passive control and a damping unit to prevent flutter.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If large wing tip devices are integrated on aircraft, then aerodynamic performance is improved, but structural loads at the wing root increase
Solution Approach 1:
The patent applies a passive torque control device that allows the wing-like element to rotate dynamically in response to aerodynamic forces. The rotatable interface means enables the wing-like element to adjust its angle of incidence automatically, transforming from a static structure to a dynamic one that can adapt to varying flight conditions and reduce peak loads at the wing root.
Solution Approach 2:
The patent changes the parameter of angle of incidence of the wing-like element by allowing rotation about a rotational axis. This parameter change is controlled passively through aerodynamic forces acting on the wing-like element itself, which create a torque that rotates the element to reduce the effective lever arm and thereby reduce structural loads at the wing root.
2Reliability
If wing tip devices are curved upwards with large angles, then aerodynamic performance is improved, but effective lever arm for load reduction is reduced
Solution Approach 1:
The patent makes the wing-like element dynamic by allowing it to rotate about a rotational axis through the rotatable interface means. This enables the effective lever arm to vary dynamically - in normal flight conditions the wing-like element maintains its aerodynamic position, but under high load conditions it rotates to reduce the lever arm and thereby reduce the bending moment at the wing root.
3Reliability
If control surfaces are integrated into wing tip devices, then load alleviation capability is improved, but integration is hindered by small planar areas and profile depths
Solution Approach 1:
The patent makes the wing-like element itself serve multiple functions: it provides aerodynamic lift enhancement and simultaneously acts as the control surface for load alleviation. By allowing the entire wing-like element to rotate about the rotational axis, the system eliminates the need for separate control surfaces, thereby reducing integration complexity while maintaining load alleviation capability.
Solution Approach 2:
The patent extracts the control function from traditional control surfaces and integrates it directly into the wing-like element's motion. The rotation of the wing-like element about the rotational axis provides the load alleviation effect without requiring additional control surfaces, thereby simplifying the overall structure and reducing integration complexity.
4Force
If passive torque control device with rotatable interface is used, then structural loads are reduced, but device complexity increases
Solution Approach 1:
The patent implements a self-service system where the wing-like element controls its own rotation through aerodynamic forces. The torque control device requires no external power source, sensors, or active control systems - the aerodynamic forces acting on the wing-like element automatically create the torque needed to rotate it to the optimal angle, thereby reducing structural loads without adding complex active control systems.
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 effectively reduces structural loads on the aircraft by adjusting the angle of incidence of the wing-like element in response to aerodynamic forces, minimizing lift and torque, thereby alleviating loads during gusts and maneuvers.
Implementation Method 1
The wing-like element is adapted to induce a rotation around the rotational axis in an air flow
Implementation Method 2
the torque control device is adapted to limit the degree of rotation depending on a torque introduced into the interface means by the wing-like element
Data Source
Figure 1a~1b
Figure 2~3a
Figure 3b~4b
AI summary
An aircraft comprises a fuselage, a wing (2) attached to the fuselage, a wing tip device (6) attached to a wing end (4) of the wing (2), at least one additional wing-like element (14) having a wing root (22), a wing leading edge (18) and a wing trailing edge (20), and a torque control device having a rotatable interface means. The torque control device is adapted for rotatably supporting the wing root of the wing-like element on the interface means under creation of a rotational axis (16) extending from the interface means into the wing-like element (14), about which rotational the wing-like element (14) is rotatable. The wing-like element (14) is adapted to induce a rotation around the rotational axis (16) in an air flow. The torque control device is adapted to limit the degree of rotation depending on a torque introduced into the interface means by the wing-like element (14) and the wing root (22) of the at least one wing-like element (14) is coupled with at least one of the wing tip device (6), the wing (2) and the fuselage through the torque control device such that the leading edge (18) extends into an airflow surrounding the aircraft.