CFRP Planked Stringers for Aircraft Wing Structural Support
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Solution Overview
Problem
Designing aircraft wing structural components that effectively manage various forces while minimizing weight and cost, particularly in composite materials, is complex due to the need to adhere to existing metallic designs, which does not fully utilize the potential of composite materials.
Innovation Solution
The use of laterally extending composite planked stringers with tapering thickness and aligned fiber orientations in Carbon Fiber Reinforced Polymer (CFRP) to bear shear and bending stresses, integrated with spars that increase in thickness towards the wing tip, providing strength against compression, tension, and torsional forces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If composite materials are used to reduce weight and increase strength, then weight reduction and strength improvement are achieved, but design complexity and manufacturing cost increase due to adherence to existing metallic designs
Solution Approach 1:
The wing structure is divided into discrete stringer components that can be independently designed and manufactured. Each stringer is a separate composite component that integrates with the skin, allowing modular design approaches that reduce overall complexity while maintaining strength and weight benefits.
Solution Approach 2:
Composite materials are used to create stringers that are both lighter and stronger than traditional metallic components. The composite construction allows for optimized fiber orientations and material distribution that meet structural requirements while reducing weight, without being constrained by metallic design paradigms.
2Weight of moving object
If composite materials are used to reduce weight and increase strength, then weight reduction and strength improvement are achieved, but manufacturing cost increases
Solution Approach 1:
By segmenting the wing structure into separate stringer components, manufacturing can be optimized for each component individually. This allows for efficient composite layup processes, potential automation, and standardized production techniques that reduce overall manufacturing cost despite using composite materials.
Solution Approach 2:
The stringer design integrates multiple functions into single components, combining structural support, skin attachment, and load-bearing functions. This integration reduces the total number of parts that need to be manufactured and assembled, thereby reducing manufacturing cost while maintaining weight and strength benefits.
3Reliability
If metallic design principles are followed, then existing design requirements are met, but the potential of composite materials is not fully utilized
Solution Approach 1:
The composite stringers utilize local quality variations through optimized fiber orientations and material properties in different regions of each stringer. This allows the structure to have varying strength and stiffness characteristics tailored to local load requirements, fully utilizing composite material potential while meeting design requirements.
Solution Approach 2:
The design employs parameter changes in material properties, fiber orientations, and stringer geometries to optimize performance. By varying these parameters according to local structural requirements, the composite materials achieve their full potential for strength and weight optimization while complying with design standards.
Data Source
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AI summary
Systems and methods are provided for structurally supporting an aircraft wing. The system comprises a section of aircraft wing that includes skin. The skin surrounds an internal volume of the wing and comprises layers of Carbon Fiber Reinforced Polymer (CFRP) having fiber orientations aligned to bear shear stresses applied to the wing. The section of aircraft wing also includes planked stringers that are laterally oriented within the wing, contact the skin within the internal volume, are attached to the skin, and comprise layers of CFRP having fiber orientations that are aligned to bear bending at the wing. Furthermore, the section includes spars that are positioned between planked stringers on an upper portion of the wing and planked stringers on a lower portion of the wing, wherein the spars are aligned with the planked stringers.