Wing Module With Non-Zero Pivot Axes for Compact Stowage
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Solution Overview
Problem
Existing air vehicles with deployable wings face challenges in efficiently transitioning between stowed and deployed configurations, particularly in maintaining compactness and aerodynamic efficiency during deployment, which affects their storage, transportation, and flight capabilities.
Innovation Solution
A wing system with deployable wing elements that pivot about non-zero angular displacement axes, allowing for a selective transition between stowed and deployed configurations, where the wing elements can be oriented non-parallel to the fuselage longitudinal axis, enabling compact storage and efficient aerodynamic lift generation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If wing elements are folded in close proximity to the fuselage for storage, then compactness and packaging efficiency are improved, but aerodynamic efficiency and flight capabilities deteriorate
Solution Approach 1:
The wing system is divided into multiple deployable wing elements that can be independently positioned. These segmented elements allow the wings to be folded into compact configurations for storage while maintaining the ability to deploy into full aerodynamic configurations for flight, resolving the contradiction between compact storage volume and aerodynamic efficiency
Solution Approach 2:
The wing elements are designed with dynamic deployment capabilities, transitioning from static folded positions to dynamic deployed positions. This dynamic characteristic allows the same wing structure to serve dual purposes: compact storage when folded and aerodynamic efficiency when deployed, eliminating the trade-off between the two states
2Volume of moving object
If wing elements are oriented parallel to the fuselage longitudinal axis for storage, then packaging efficiency is improved, but stability and control moments deteriorate
Solution Approach 1:
The wing elements utilize angular displacement about pivot axes that are non-zero relative to the fuselage longitudinal axis. This dimensional change in orientation allows the wings to achieve compact packaging when folded parallel to the fuselage while maintaining the geometric configuration necessary for stability and control moments when deployed at angled orientations
3Device complexity
If simple folding mechanisms are used for wing deployment, then device complexity is reduced, but aerodynamic performance and deployment efficiency deteriorate
Solution Approach 1:
The deployment mechanism employs nested pivot axes where inner pivot axes are contained within or coupled to outer pivot axes. This nesting arrangement achieves complex aerodynamic deployment sequences through coordinated rotation about multiple pivot points, delivering high deployment efficiency and aerodynamic performance while keeping the overall mechanism relatively simple and integrated
Data Source
AI summary
A wing system is provided for an air vehicle, having a fuselage including a fuselage section and a fuselage longitudinal axis. The wing system has at least one wing deployment module, each including a set of wing elements, including at least a first wing element having a first longitudinal axis, and a second wing element having a second longitudinal axis. Each wing deployment module is configured for selectively transitioning between a stowed configuration and a deployed configuration. In the stowed configuration, the first wing element and the second wing element are in overlying relationship such that the first longitudinal axis and the second longitudinal axis are nominally parallel with one another. In the deployed configuration, the first wing element is oriented with respect to the second wing element such that the first longitudinal axis is non-parallel with respect to the second longitudinal axis.