Aircraft Crown Integration Panel With Dual-Bracketed Support
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Solution Overview
Problem
Existing secondary support structures for aircraft crown portions are costly, labor-intensive to install, and inefficiently utilize space, with manual adjustments required for build tolerances, leading to increased weight and complexity.
Innovation Solution
A dual-bracketed support system with a crown integration panel (CIP) using a honeycomb panel and sheet metal, featuring adjustable fittings and self-aligning attachments, allowing for external assembly and alignment of aircraft equipment, reducing the need for specialized fasteners and manual adjustments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a lattice structure is used to support equipment and furnishings in the aircraft crown portion, then the structure can provide stable and variable configurations, but the structure becomes expensive, heavy, and difficult to install
Solution Approach 1:
The support structure is divided into modular units (lattice modules) that can be independently manufactured and assembled. Each module contains standardized connection points and can be configured in different arrangements to support various equipment configurations, reducing the need for a complete heavy lattice structure while maintaining adaptability
Solution Approach 2:
The lattice modules are designed with universal connection interfaces and standardized mounting points that can accommodate different types of equipment and furnishings. The same modular structure serves multiple functions: structural support, equipment mounting, and configurable spatial organization, eliminating the need for separate specialized structures
2Adaptability or versatility
If a lattice structure is installed inside the aircraft to support equipment, then the structure can be assembled, but the installation process becomes time-consuming and labor-intensive requiring numerous installation personnel
Solution Approach 1:
The support structure is segmented into pre-fabricated modular units that can be assembled outside the aircraft and then quickly installed as complete modules. This reduces the number of small assembly operations required inside the aircraft and minimizes installation time and personnel requirements
Solution Approach 2:
The lattice modules are pre-assembled and pre-configured outside the aircraft before installation. Equipment can be pre-mounted to the modules in controlled shop environments, allowing for quality control and configuration verification before the modules are installed in the aircraft, thereby reducing on-site installation time and complexity
3Ease of manufacture
If sheet metal construction is used for support brackets and trays, then the components are easy to manufacture and provide electrical conductivity, but larger scale components require progressively more stiffening elements increasing cost and weight
Solution Approach 1:
The support structure utilizes composite materials such as honeycomb panels combined with metal skins or frames. These composites provide high stiffness-to-weight ratios, allowing larger scale support structures without requiring excessive stiffening elements. The metal components retain electrical conductivity while the honeycomb core provides structural rigidity
4Weight of stationary object
If composite structures are used for larger support panels, then the weight is reduced, but specialized hardware is required to interface with attached equipment and additional provisions are needed for grounding and bonding
Solution Approach 1:
The composite panels are designed with integrated metal attachment hardware and grounding provisions built into the panel structure itself. Mounting points, fastener interfaces, and electrical grounding paths are incorporated during panel manufacturing rather than requiring separate attachment components, thereby reducing interface complexity while maintaining weight benefits
5Adaptability or versatility
If manual-adjustment features are incorporated into secondary structure attachments to compensate for build tolerances, then the structure can accommodate variations, but additional costs and labor are introduced
Solution Approach 1:
The attachment system incorporates adjustable parameters such as variable-length tie rods, adjustable bracket positions, and flexible mounting configurations that can be tuned to accommodate build tolerances. These adjustments are designed to be simple and standardized, reducing the complexity compared to complex mechanical adjustment mechanisms while still providing the necessary tolerance compensation
Data Source
Figure 1
Figure 2A~2B
Figure 3
AI summary
A dual-bracketed support system and a corresponding method are disclosed. The dual-bracketed support system includes (i) a first bracket connected to a support structure for a crown portion of an aircraft, (ii) a second bracket, and (iii) a support rod having a proximal end and a distal end. The proximal end is connected to the first bracket and the distal end is connected to the second bracket. The second bracket is configured to allow the support rod to translate along a longitudinal axis defined by the support rod.