Deployable Wing Module Layout for Compact Launch and Stable Flight
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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 aerodynamic efficiency and minimizing interference during deployment.
Innovation Solution
A wing system for air vehicles featuring deployable wing elements that transition from a stowed to a deployed configuration using a deployment system, with each wing module comprising a first and second wing element, allowing for aerodynamic lift generation and controlled movement via actuators and pivot axes to minimize interference.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If wings are folded in close proximity to the fuselage for launch, then the air vehicle can be accommodated in a tubular launcher, but aerodynamic efficiency is reduced during flight
Solution Approach 1:
The wing system is divided into multiple deployable wing modules that can be independently folded and deployed. Each module contains wing elements that can be segmented for compact storage and then reconfigured for aerodynamic flight, resolving the contradiction between compact stowed volume and aerodynamic efficiency.
Solution Approach 2:
The wing system transitions from a static folded configuration to a dynamic deployed configuration through actuated movement. The wings are designed to be dynamically reconfigurable, allowing the air vehicle to optimize its aerodynamic properties for different flight phases while maintaining compact dimensions during launch.
2Speed
If wings are deployed rapidly from tubular launcher, then launch efficiency is improved, but aerodynamic characteristics become unstable during transition
Solution Approach 1:
The wing modules are pre-configured in a folded state within the tubular launcher, with all necessary components positioned for rapid deployment. The actuation system is pre-loaded and ready to deploy the wings in a controlled sequence, ensuring both speed and stability during the transition from launch to flight configuration.
3Productivity
If multiple wing elements are used for aerodynamic lift, then flight performance is improved, but device complexity increases
Solution Approach 1:
Multiple wing elements are nested within each other in a compact arrangement during stowed configuration. The wing modules contain nested structural components that can be sequentially deployed, allowing multiple aerodynamic surfaces to be packed into a small volume while maintaining the capability for complex flight maneuvers when deployed.
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
Enables efficient aerodynamic lift generation and reduced interference during deployment, enhancing flight performance and operational flexibility of air vehicles.
Implementation Method 1
A coil spring may provide both torsion and compression forces to rotate the fin into the deployed position and lock it into place
Implementation Method 2
A coil spring may provide both torsion and compression forces to rotate the fin into the deployed position and lock it into place
Data Source
Figure 1
Figure 2
Figure 2(a)
AI summary
A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage section and a fuselage longitudinal axis, the wing system having at least one wing deployment module. Each wing deployment module includes a set of wing elements, including at least a first wing element having a first wing element longitudinal axis, and a second wing element having a second wing element longitudinal axis. Each wing deployment module is configured for selectively transitioning between a respective stowed configuration and a respective deployed configuration. In the stowed configuration, the first wing element and the second wing element are in overlying relationship such that the first wing element longitudinal axis and the second wing element 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 wing element longitudinal axis is non-parallel with respect to the second wing element longitudinal axis.