Flapping Wing Strut Assembly for Aerodynamic Force Distribution
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Solution Overview
Problem
Current wing designs for flapping wing aircraft lack optimal aerodynamic efficiency, particularly in distributing aerodynamic forces and managing air displacement during upstroke and downstroke movements.
Innovation Solution
The wing features a strut arrangement with main and supporting struts made of fiber-reinforced plastic, where the supporting struts are aligned at angular intervals and connected to a pivot-bearing main strut, allowing for elastic deformation and torque application, combined with planking members that adjust air displacement based on wing movement, mimicking bird wing flapping mechanics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the wing uses a rigid structure for the entire wing body, then the structural strength is improved, but the aerodynamic efficiency and ability to deform like a bird's wing deteriorates
Solution Approach 1:
The wing is divided into a rigid front portion and a flexible rear portion. The rigid front portion provides structural strength and stability, while the flexible rear portion can deform during flapping movements to improve aerodynamic efficiency. This segmentation allows each part to perform its optimal function without compromising the other.
Solution Approach 2:
Different parts of the wing have different mechanical properties. The front portion is made rigid to maintain structural integrity during flight, while the rear portion is made flexible to allow deformation during flapping. This local differentiation of material properties resolves the contradiction between overall strength and localized deformability.
2Productivity
If the wing uses flexible materials throughout, then the aerodynamic efficiency and bird-like deformation are improved, but the structural stability and force distribution deteriorates
Solution Approach 1:
The wing is segmented into a rigid front portion and a flexible rear portion. The rigid front portion maintains structural stability and provides a stable base for force distribution, while the flexible rear portion achieves aerodynamic efficiency through deformation during flapping movements.
Solution Approach 2:
The wing uses composite construction combining rigid and flexible materials in specific regions. This allows the front portion to provide structural stability while the rear portion provides aerodynamic efficiency, resolving the contradiction between stability and deformability.
3Ease of manufacture
If the support struts are arranged perpendicular to the main strut, then the manufacturing simplicity is improved, but the aerodynamic force distribution and torque application deteriorates
Solution Approach 1:
The support struts are arranged at specific angular intervals (30-90 degrees) relative to the main strut, creating localized zones of optimized force distribution. This angular arrangement allows each strut to apply torque effectively to the main strut, improving aerodynamic force distribution while maintaining manufacturing simplicity through standardized angular spacing.
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 enhances aerodynamic efficiency by ensuring homogeneous force distribution, optimal air displacement, and reduced material costs through the use of standard components, achieving a deformation behavior similar to a bird's wing, thereby improving lift and propulsion.
Implementation Method 1
the support strut is deformed exclusively elastically by the action of aerodynamic forces when the wing is used as intended
Implementation Method 2
the support struts are made of a fiber-reinforced plastic material in order to achieve an advantageous compromise in terms of weight and stability
Data Source
AI summary
A wing for use in a flapping wing aircraft, having a strut assembly including a main strut and a plurality of support struts each oriented at an angular interval between 30 degrees and 90 degrees with respect to the support strut, at least a section of the support struts having a front section, a connecting section adjacent thereto, and a rear section adjacent thereto, and wherein each of said support struts is secured to said main strut by said connecting section, and further having a group of planking members made of a resilient and dimensionally stable sheet material and connected to said strut assembly.