Float-Wing Buoyancy and Lift Integration for Aircraft Weight Reduction
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Solution Overview
Problem
Aircraft designed for water landings face challenges with weight and cost due to dedicated booms or floats, which increase weight and are aerodynamically undesirable, while existing designs are complex and power-intensive.
Innovation Solution
The development of float-wings with airfoil shapes that provide both buoyancy and lift, featuring rotatable wings that can switch between hovering and forward flight configurations using fixed rotors, reducing complexity and weight, and utilizing lightweight materials for buoyancy and lift.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a dedicated boom or float is added to provide buoyancy, then the aircraft can land on water, but the weight and cost increase
Solution Approach 1:
The patent combines the buoyancy function with the wing structure by making the wing itself buoyant through airfoil shape and hollow construction, eliminating the need for separate dedicated booms or floats. This merging of functions reduces overall weight while maintaining water landing capability.
Solution Approach 2:
The wing is designed to serve multiple functions: providing aerodynamic lift during flight, providing buoyancy during water operations, and serving as a structural support element. This multi-functionality eliminates the need for specialized equipment, reducing weight and cost.
2Adaptability or versatility
If a dedicated boom or float is added to provide buoyancy, then the aircraft can land on water, but the aerodynamic performance deteriorates
Solution Approach 1:
By merging the buoyancy function into the aerodynamic wing structure itself, the design eliminates separate buoyancy devices that would create aerodynamic drag. The wing's airfoil shape provides both lift and buoyancy without additional aerodynamic penalties.
Solution Approach 2:
The wing structure is designed to universally provide both aerodynamic lift and buoyant force, eliminating the need for specialized buoyancy equipment that would interfere with aerodynamic performance during flight.
3Device complexity
If fixed rotors are used for vertical takeoff and forward flight, then the device complexity is reduced, but the adaptability between flight modes must be maintained
Solution Approach 1:
The patent employs dynamically adjustable wing configurations that can change orientation and angle of attack to accommodate different flight modes. The wings can rotate and reposition themselves to optimize performance for both vertical takeoff and forward flight using fixed rotors.
Solution Approach 2:
The fixed rotor configuration combined with multi-functional wing design allows the same rotor system to serve both vertical lift and forward propulsion functions, maintaining adaptability between flight modes without requiring complex variable geometry mechanisms.
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
This design allows for efficient vertical takeoff and transition to forward flight with reduced power consumption, eliminating the need for specialized equipment and minimizing weight and cost, while providing both buoyancy and lift, thus enhancing aerodynamic efficiency and reducing complexity.
Implementation Method 1
The float-wing also includes a submersible part that includes at least the trailing edge and is (generally speaking) buoyant
Implementation Method 2
The float-wing has an airfoil shape to produce aerodynamic lift when the float-wing flows through air at a lift-producing angle of attack in a forward flight mode of operation
Data Source
AI summary
An aircraft which includes a float-wing having a leading edge, a trailing edge, and an airfoil shape to produce aerodynamic lift when the float-wing flows through air at a lift-producing angle of attack in a forward flight mode of operation. The float-wing further includes a submersible portion that includes at least the trailing edge and which is constructed of materials and in a shape selected to produce a buoyancy force sufficient to prevent at least a non-submersible portion of the aircraft from being submersed under conditions in which the aircraft is in a waterborne non-flight position in which at least the trailing edge of the float-wing is submersed but at least the non-submersible portion of the aircraft is not submersed.