Variable Aspect Ratio Deployable Wings for Aerial Vehicles
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Solution Overview
Problem
Existing aerodynamic vehicles face challenges in achieving variable aspect ratios for their wings, which are crucial for optimizing lift and drag ratios, while also requiring compact storage and efficient deployment mechanisms, often resulting in complex and costly flight control systems.
Innovation Solution
A deployable wing arrangement that includes a fuselage with a carriage and wing assemblies that can pivot and telescope, allowing for the adjustment of aspect ratio during flight by deploying and retracting wing panels, enabling a flexible wing configuration suitable for various mission requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If deployable wings are used to increase aspect ratio for extended range, then flight distance and loiter time are improved, but device complexity and cost increase due to mechanical transmission requirements
Solution Approach 1:
The control surfaces on the deployable wings are designed to be self-contained with integrated actuators that do not require external mechanical transmission systems. The wings deploy and function independently with their own control mechanisms, eliminating the need for complex fuselage-mounted transmission systems and reducing overall device complexity while maintaining extended range capability
Solution Approach 2:
The wing assembly is divided into multiple segments that can deploy independently, with each segment containing its own control surfaces and actuators. This segmentation allows the wings to function as self-contained units, reducing the mechanical transmission complexity that would otherwise be required to connect control systems from the fuselage to the deployable wings
2Speed
If conventional cantilevered wings are used for maneuverability, then speed and cruise range are improved, but storage volume and physical envelope increase
Solution Approach 1:
The wing configuration transitions from a fixed conventional design to a dynamic deployable system. The wings can be deployed to high aspect ratio configurations for long-range missions or retracted to compact configurations for storage, allowing the vehicle to adapt its aerodynamic characteristics to mission requirements while maintaining compact physical envelope when not in use
3Ease of operation
If actators are mounted on fuselage for control actuation, then control capability is maintained, but device complexity increases due to mechanical transmission across joints
Solution Approach 1:
Each wing assembly contains its own actuators mounted directly on the wing structure rather than requiring actuators to be mounted on the fuselage and transmit force through mechanical linkages. This self-contained approach eliminates the complex mechanical transmission across joints while maintaining full control capability for the deployable wings
Data Source
AI summary
Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.