Trifold Wing Pivot Column Retention Mechanism

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Unmanned aerial vehicles (UAVs) face challenges in quickly and reliably converting control surfaces between stowed and deployed configurations, which complicates storage and portability, and requires a mechanism to manage heavier actuator components within the fuselage without interfering with weight distribution or aerodynamics.

Innovation Solution

A control surface assembly that includes a pivot column and joint arrangement allowing the trifold wing to rotate from a stowed to a deployed position, with a control surface linkage that operates the control surface in both configurations without stressing the linkage or fin, and an actuator located within the fuselage to maintain optimal weight distribution.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If control surfaces are deployed for proper UAV operation, then flight capability is improved, but storage and portability are worsened due to increased size and complexity

Engineering Contradiction:

Improveflight capabilityVSAvoidstorage volume

Core Design Contradiction:

Adaptability or versatilityVSVolume of moving object

Solution Approach 1:

The control surfaces are designed to fold and nest within the fuselage body when not in use, similar to how nested dolls store within each other. The wing panels fold along hinge lines to reduce their span, allowing them to be stored compactly within the fuselage volume during transport while being fully deployable for flight operations.

Inventive Principle:

Principle #7Nested doll (Nesting)

Solution Approach 2:

The control surfaces transition between static stored configuration and dynamic deployed configuration through hinge joints and actuation mechanisms. This allows the structure to adapt its shape and volume based on operational requirements, being compact for storage and extended for flight.

Inventive Principle:

Principle #15Dynamics

2Adaptability or versatility

If multiple fins with control surfaces are added for proper UAV operation, then flight control capability is improved, but device complexity is worsened

Engineering Contradiction:

Improveflight control capabilityVSAvoidstructural complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

Multiple control surface functions are combined into integrated fin assemblies that share common mounting structures and actuation systems. The fins are consolidated into unified structures rather than separate independent components, reducing overall structural complexity while maintaining full flight control capability.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The fin and control surface assemblies are designed to serve multiple functions: providing aerodynamic control, structural support, and compact storage capability. The same structures that provide flight control also serve as the folding mechanism and storage framework, eliminating the need for separate dedicated components.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Weight of moving object

If actuator components are placed within the fuselage for optimal weight distribution, then weight balance is improved, but access and maintenance difficulty increases

Engineering Contradiction:

Improveweight distributionVSAvoidactuator maintenance

Core Design Contradiction:

Weight of moving objectVSEase of repair

Solution Approach 1:

The actuation system is divided into modular segments with standardized interfaces. Each actuator is a self-contained module that can be independently accessed, removed, and replaced. The segmentation allows actuators to be positioned optimally within the fuselage for weight balance while maintaining ease of maintenance through modular design.

Inventive Principle:

Principle #1Segmentation

4Productivity

If control surfaces are quickly converted between stowed and deployed configurations, then productivity is improved, but reliability is worsened due to increased stress on linkage and fin

Engineering Contradiction:

Improvedeployment speedVSAvoidlinkage durability

Core Design Contradiction:

ProductivityVSReliability

Solution Approach 1:

The control surfaces are pre-positioned and pre-aligned in their stowed configuration with all linkage components pre-assembled and pre-stressed. This preliminary preparation ensures that when deployment is initiated, the transition occurs smoothly without sudden stress spikes or misalignment, maintaining both speed and reliability.

Inventive Principle:

Principle #10Preliminary action

Data Source

PatentUS10442521B1Apparatus for retaining and deploying a wing of an aerial vehicle

Publication Date: 2019.10.15 LOCKHEED MARTIN CORP

AI summary

An apparatus, having: a fuselage body section (180) configured to be secured to an aircraft fuselage (16); a pivot column (310) protruding from the fuselage body section; and a center wing section (214) configured to be secured to a center wing panel of a trifold wing (200). The fuselage body section and the center wing section are configured to cooperate with each other to rotate the center wing section relative to the fuselage body section from a stowed position (250) to a deployed position (302). The pivot column comprises a column feature (240) configured to engage with tip features (236) of the trifold wing to hold the trifold wing in a folded configuration when the trifold wing is in the stowed position and to disengage from the tip features as the trifold wing rotates to the deployed position, thereby freeing the trifold wing to unfold.