Composite Airfoil Trailing Edge Profile Reduces Parasitic Drag
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Solution Overview
Problem
Current aircraft airfoil trailing edge profiles require extensive use of epoxy filler to reduce parasitic drag, which increases weight, cost, and lead time due to curing and finishing processes, and poses challenges during maintenance and repair.
Innovation Solution
A U or V shaped profile made of composite material with recesses that reduce the need for filler and rivets, providing a lightweight, aerodynamically efficient solution that can be easily repaired by replacing damaged sections without the need for extensive disassembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If epoxy filler is added to the profile joint, then parasitic drag is reduced, but weight increases and lead time increases due to curing and finishing processes
Solution Approach 1:
The patent removes the epoxy filler from the profile joint design, extracting the harmful element that causes parasitic drag while eliminating the associated curing and finishing processes that extend lead time. The solution achieves aerodynamic efficiency through the profile geometry itself without requiring filler materials.
Solution Approach 2:
The patent changes the design parameters of the profile joint to eliminate the need for filler. By optimizing the profile geometry and rivet configuration, the solution achieves the desired aerodynamic properties without the time-consuming curing and finishing processes required by epoxy filler.
2Object-generated harmful factors
If epoxy filler is added to the profile joint, then parasitic drag is reduced, but manufacturing cost increases due to hand labor hours
Solution Approach 1:
The patent removes the epoxy filler from the profile joint design, extracting the harmful element that causes parasitic drag while eliminating the associated hand labor hours for application, curing, sanding, and polishing. This extraction directly reduces manufacturing cost while maintaining aerodynamic efficiency.
3Object-generated harmful factors
If epoxy filler is added to the profile joint, then parasitic drag is reduced, but reliability decreases due to stress-induced cracks
Solution Approach 1:
The patent removes the epoxy filler from the profile joint design, extracting the harmful element that causes parasitic drag while eliminating the source of stress-induced cracks. By eliminating the filler material, the solution removes the weak point that compromises reliability under atmospheric stress.
4Strength
If traditional metallic profile is used to join two airfoil pieces, then structural strength is maintained, but weight increases and parasitic drag increases
Solution Approach 1:
The patent employs composite materials for the profile joint, combining materials that provide sufficient structural strength while significantly reducing weight compared to traditional metallic profiles. This composite approach maintains the necessary mechanical properties while eliminating the weight and drag penalties of metal construction.
Data Source
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AI summary
The present invention belongs to the field of aeronautical structures such as an aircraft airfoil, and in particular to the profiles that are coupled to a trailing edge of an airfoil. In addition, the present invention provides a method to repair the trailing edge profile of an aircraft airfoil.