Morphing Wing Linkage With Streamlined Feathers for Aerodynamics

Solution Overview

Problem

Conventional morphing wings lack a streamlined shape in their deployed state, resulting in inferior aerodynamic performance compared to traditional airplane wings.

Innovation Solution

A morphing wing structure featuring a link mechanism that deploys and retracts, with streamlined front wing covers and flight feathers that rotate and adjust to minimize size and maximize lift, and a flight control system using deep reinforcement learning for efficient flight control.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If conventional flat components are simply overlapped in deployed state, then the structure is simple to manufacture, but aerodynamic performance is greatly inferior

Engineering Contradiction:

Improveease of manufactureVSAvoidaerodynamic performance

Core Design Contradiction:

Ease of manufactureVSReliability

Solution Approach 1:

The patent applies curvature by designing the wing components with streamlined shapes that follow aerodynamic contours. The front wing cover, flight feathers, and rear wing cover are all designed with curved surfaces that reduce drag and improve airflow, transforming the flat simple structures into aerodynamically efficient components while maintaining manufacturing feasibility.

Inventive Principle:

Principle #14Spheroidality (Curvature)

Solution Approach 2:

The patent implements dynamics through the link mechanism that enables the wing to transition between deployed and retracted states. The flight feathers are rotatably mounted and can adjust their angles dynamically based on flight conditions, allowing the wing to adapt its shape for optimal aerodynamic performance during different flight phases.

Inventive Principle:

Principle #15Dynamics

2Adaptability or versatility

If flight feathers are mounted on link mechanism, then position and orientation can be controlled, but device complexity increases

Engineering Contradiction:

Improveposition and orientation controlVSAvoiddevice complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The patent applies segmentation by dividing the wing into multiple independent components: front wing cover, multiple flight feathers, rear wing cover, and link mechanism. Each flight feather can be independently mounted and rotated, allowing individual control of position and orientation. This modular segmentation enables precise aerodynamic control while keeping each component relatively simple in structure.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent implements dynamics through the link mechanism that enables the wing to transition between deployed and retracted states. The flight feathers are rotatably mounted and can adjust their angles dynamically based on flight conditions, allowing the wing to adapt its shape for optimal aerodynamic performance during different flight phases.

Inventive Principle:

Principle #15Dynamics

3Reliability

If wing components are streamlined shape, then aerodynamic performance is improved, but manufacturing complexity increases

Engineering Contradiction:

Improveaerodynamic performanceVSAvoidmanufacturing complexity

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

The patent applies curvature by designing the wing components with streamlined shapes that follow aerodynamic contours. The front wing cover, flight feathers, and rear wing cover are all designed with curved surfaces that reduce drag and improve airflow, transforming the flat simple structures into aerodynamically efficient components while maintaining manufacturing feasibility.

Inventive Principle:

Principle #14Spheroidality (Curvature)

Data Source

PatentUS20240286730A1Morphing wing, flight control device, flight control method, and program

Publication Date: 2024.08.29 JAPAN AEROSPACE EXPLORATION AGENCY

AI summary

A morphing wing (140) of the present invention includes a link mechanism configured to be deployed in a first direction and retracted in a second direction opposite to the first direction, a plurality of front wing covers (180) mounted on a front side which is one side of the link mechanism perpendicular to the first direction, and a plurality of flight feathers (160) mounted on a rear side which is the other side of the link mechanism perpendicular to the first direction, wherein the front wing covers (180) and the flight feathers (160) are streamlined from the front side toward the rear side, and when the link mechanism is retracted, the flight feathers (160) are retracted inside the adjacent flight feathers (160).