Nacelle Panel Link Assembly for Tight Actuator Attachment Space
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Solution Overview
Problem
Existing thrust reversers face challenges in attaching actuators due to limited space between inner and outer panels, especially with engines having high expansion ratios and closer aerodynamic lines, leading to complications in mechanical behavior and space constraints.
Innovation Solution
An assembly comprising a nacelle panel with an outer and inner skin, a central layer, and a member forming a link attached to the panel via at least one skin, utilizing a free inner enclosure and optional reinforcement to minimize space requirements and distribute stress, allowing actuator attachment without passing through the panel's entire thickness.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If attachments pass through the entire panel thickness to connect the actuator, then the actuator can be securely attached, but the space between inner and outer panels is insufficient and the panel structure becomes overly complex
Solution Approach 1:
The attachment member extends only partially through the panel thickness rather than completely, utilizing a dimensional approach where the attachment occurs at a specific depth within the panel rather than spanning the entire thickness. This allows secure attachment while preserving space between the inner and outer panels.
Solution Approach 2:
The panel attachment system is segmented into multiple components: the panel itself, the attachment member that extends partially through the panel, and the reinforcement element. This segmentation allows each component to perform its specific function while collectively solving the space constraint problem.
2Volume of moving object
If the panel thickness is reduced locally to accommodate the attachment fitting, then space is saved, but the mechanical behavior of the panel is degraded
Solution Approach 1:
Reinforcement is applied locally at the attachment area rather than throughout the entire panel. The reinforcement element is positioned specifically where the attachment member connects to the panel, providing localized strength enhancement without adding unnecessary weight or complexity elsewhere in the structure.
Solution Approach 2:
The solution employs a composite structure combining the panel material with a reinforcement element made of different material properties. This composite approach allows the reinforcement to compensate for the localized thickness reduction while maintaining the overall panel design.
3Reliability
If densified honeycomb is used to reinforce the panel area, then attachment reliability is improved, but the weight of the panel increases
Solution Approach 1:
Instead of using densified honeycomb throughout the panel, the reinforcement is applied locally only at the attachment area. This localized reinforcement provides the necessary attachment reliability while minimizing the additional weight that would result from densifying the entire honeycomb structure.
Solution Approach 2:
The reinforcement element serves as a dedicated, localized component that provides reinforcement only where needed. Rather than modifying the entire honeycomb structure to be densified, this separate reinforcement element can be optimized independently for its specific function at the attachment point.
Data Source
AI summary
An assembly including a nacelle panel of an aircraft engine, the nacelle panel including an outer skin, an inner skin and a central layer interposed between the outer skin and the inner skin, and the nacelle panel having a free inner enclosure contiguous with the outer skin, and a member forming a link including one or more degrees of freedom, the member being attached to the nacelle panel solely by one or both of the outer skin and the inner skin, and the member extending facing the free inner enclosure.