Adjustable Wingtip Toe Angle Control for Variable Flight Efficiency

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Solution Overview

Problem

Existing aircraft winglets are optimized for specific flight conditions, leading to trade-offs between performance and weight, and fail to adjust to varying flight conditions, thus reducing overall efficiency.

Innovation Solution

An adjustable lift modification wingtip with a horizontal and vertical portion, equipped with a control surface, that can adjust its toe angle and deflection to optimize lift distribution based on flight conditions, using a control system to coordinate these adjustments.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If winglets are designed with additional structure to handle higher performance loads, then performance is improved, but weight increases

Engineering Contradiction:

ImproveperformanceVSAvoidweight

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The patent applies dynamics by making the winglet structure movable and adjustable rather than fixed. The winglet can change its angle and position dynamically to adapt to different flight conditions, allowing it to handle varying loads without requiring excessive structural weight for maximum performance scenarios.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The patent changes physical parameters of the winglet, specifically its angle relative to the wing and its position along the wing span. By adjusting these parameters, the winglet can optimize performance for different flight conditions without requiring a heavy fixed structure designed for the most extreme scenario.

Inventive Principle:

Principle #35Parameter changes

2Reliability

If winglets are optimized for one flight condition, then performance at that condition is improved, but efficiency in other flight conditions deteriorates

Engineering Contradiction:

Improveperformance at specific flight conditionVSAvoidefficiency across flight conditions

Core Design Contradiction:

ReliabilityVSAdaptability or versatility

Solution Approach 1:

The winglet is designed with dynamic adjustment capabilities, allowing it to change its configuration based on flight conditions. This enables the winglet to maintain optimal performance across different flight phases rather than being fixed for a single condition.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The winglet is designed to perform multiple functions across different flight conditions by adjusting its angle and position. It can optimize for cruise efficiency, takeoff performance, and landing configurations, making it a universal solution for various flight scenarios rather than being specialized for one condition.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Ease of manufacture

If fixed winglet structure is used, then manufacturing is simplified, but adaptability to different flight conditions is reduced

Engineering Contradiction:

Improvemanufacturing simplicityVSAvoidadaptability to flight conditions

Core Design Contradiction:

Ease of manufactureVSAdaptability or versatility

Solution Approach 1:

The patent introduces dynamic adjustment mechanisms that allow the winglet to change its configuration. While this adds some complexity compared to a fixed structure, the adjustment mechanisms are designed to be integrated into the winglet assembly, maintaining reasonable manufacturability while significantly improving adaptability.

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS20260070653A1Adjustable lift modification wingtip

Publication Date: 2026.03.12 TAMARACK AEROSPACE GROUP INC

AI summary

An adjustable lift modification wingtip may be attached to a baseline wing of an aircraft. The adjustable lift modification wingtip may comprise a horizontal portion including a control surface and a vertical portion coupled to the horizontal portion. The vertical portion may move about an axis that may be substantially perpendicular to the horizontal portion. The control surface and the vertical portion may be adjusted in conjunction to increase wing efficiency at a flight condition.