Aircraft Wing Droop Nose Assembly With Flexible Skin Actuation
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Solution Overview
Problem
Existing droop nose assemblies for aircraft wings suffer from aerodynamic inefficiencies due to discontinuities and complex actuation systems, such as those of the spigot, and the aerodynamic pressure profile, and inefficient actuation systems, such as steps or discontinuities in the transition between the high lift high technologies, such as those of the high lift body and the high lift assembly, the high lift body and the main wing, leading to aerodynamic pressure discontinuities and complex actuation systems.
Innovation Solution
A wing design with a droop nose assembly featuring a linkage system with rotatable link elements and a rotary actuator, utilizing a groove and spigot mechanism for smooth movement, eliminating discontinuities and simplifying the actuation system, and enabling synchronized movement through a sync arrangement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a traditional droop nose assembly is used to increase lift, then the wing profile curvature is increased, but discontinuities and steps appear at the transition between the high lift body and the main wing, causing aerodynamic pressure peaks
Solution Approach 1:
The patent employs a flexible skin portion that continuously deforms between stowed and deployed states, eliminating sharp edges and steps. The flexible skin is stretched over a rigid portion with rounded contours, creating a smooth aerodynamic surface that avoids pressure peaks while maintaining the necessary droop nose curvature for lift enhancement.
Solution Approach 2:
The patent uses a flexible skin portion whose deformation state changes continuously as the droop nose assembly transitions between stowed and deployed positions. This continuous parameter change in skin deformation eliminates discontinuities in the wing profile, maintaining smooth aerodynamic flow and preventing pressure peaks.
2Manufacturing precision
If complex actuation systems are used to control the high lift body, then the droop nose can be positioned accurately, but the device complexity and maintenance requirements increase
Solution Approach 1:
The patent extracts the complex actuation mechanisms from the droop nose assembly design, using instead a simplified system where the flexible skin portion's elastic deformation naturally guides the rigid portion to its correct position. The connection assembly uses basic hinge joints and flexible material properties rather than complex mechanical actuators, reducing device complexity while maintaining positioning accuracy.
Solution Approach 2:
The flexible skin portion serves as both a structural element and an actuation mechanism. Its elastic deformation properties automatically guide the droop nose assembly through the transition from stowed to deployed position, eliminating the need for complex external actuation systems. The system uses the material's inherent properties to achieve positioning.
3Shape
If the high lift body is sealed to the leading edge portion, then the wing profile is streamlined, but the connection assembly becomes more complex
Solution Approach 1:
The patent uses a flexible skin portion that acts as a sealed connection between the rigid droop nose body and the main wing leading edge. This flexible membrane creates a smooth, streamlined transition while using simple hinge connections and elastic deformation rather than complex mechanical sealing systems, reducing connection assembly complexity.
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 design achieves a smooth, aerodynamically advantageous wing profile with efficient actuation, reduced maintenance, and cost-effective operation by eliminating discontinuities and simplifying the actuation system, while allowing synchronized movement of the high lift body.
Implementation Method 1
The flexible skin portion is configured to be deformed, preferably elastically deformed, between a stowed deformation state and a deployed deformation state
Data Source
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AI summary
Disclosed is a wing (5) for an aircraft (1), comprising a main wing (11) and a leading edge high lift assembly (13) comprising a high lift body (15) and a connection assembly (17) connecting the high lift body (15) to the main wing (11) in such a way that the high lift body (15) is movable between a stowed position and a deployed position, wherein the connection assembly (17) comprises a linkage (18) including a first link element (19) that is mounted to the high lift body (15) and that is mounted to the main wing (11) rotatably about a first axis of rotation (21), wherein the main wing (11) comprises an upper skin panel (31) and a lower skin panel (33), wherein the upper skin panel (31) has a leading edge portion (35), wherein the high lift body (15) comprises a rigid portion (30) and a flexible skin portion (32), wherein the rigid portion (30) is mounted to the first link element (19), wherein the flexible skin portion (32) is connected to the leading edge portion (35) of the upper skin panel (31) of the main wing (11) and is connected to the rigid portion (30) of the high lift body (15), and wherein the flexible skin portion (32) is configured to be deformed between a stowed deformation state and a deployed deformation state, when the high lift body (15) is moved between the stowed position and the deployed position, wherein the connection assembly (17) comprises a drive unit (47) for driving the first link element (19) for rotation about the first axis of rotation (21). The object to provide a wing having a very simple and efficient leading edge high lift assembly with an advantageous aerodynamic pressure profile and a simple and efficient actuation system, is achieved in that the rigid portion (30) is mounted to the first link element (19) rotatably about a second axis of rotation (22), wherein the drive unit (47) comprises a rotary actuator (49) mounted to the main wing (11) and having at least one drive arm (51) rotatably driven about a drive axis (53) and drivingly engaging the first link element (19), wherein one of the drive arm (51) and the first link element (19) comprises at least one groove (55) and the other one of the drive arm (51) and the first link element (19) comprises at least one spigot (59) drivingly engaging the groove (55).