Landing Gear HUMS Integration via Structural Nesting
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Solution Overview
Problem
Existing health and usage monitoring systems (HUMS) for aircraft are complex, heavy, interfere with aircraft systems, generate aero-acoustic noise, and are challenging to retrofit, particularly due to the need for dedicated casings and external connections.
Innovation Solution
The HUMS components are housed within a structural subassembly of the aircraft landing gear assembly, with an access port allowing maintenance without disassembly, using the subassembly as a protective casing and EMI shield, eliminating the need for dedicated casings and reducing noise, and enabling self-contained operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If HUMS components are housed within a structural subassembly cavity, then device complexity and weight are reduced by eliminating dedicated casings, but the structural subassembly must be modified to include an access port
Solution Approach 1:
The patent merges the HUMS housing function with the existing structural subassembly of the landing gear. The structural subassembly's cavity is utilized to house HUMS components, eliminating the need for a separate dedicated casing. This integration reduces overall device complexity and weight while leveraging the existing structural component's strength and form factor.
Solution Approach 2:
The patent segments the structural subassembly by introducing an access port that allows the HUMS system to be divided into removable components. This segmentation enables the HUMS to be installed and maintained as a line replaceable unit without disassembling the entire structural subassembly, facilitating ease of maintenance while maintaining structural integrity.
2Ease of operation
If HUMS components are mounted externally on the landing gear assembly, then access for maintenance is improved, but aero-acoustic noise increases due to exposure to incident airflow
Solution Approach 1:
The patent nests the HUMS components within the cavity of the structural subassembly, which is part of the landing gear assembly. This nested configuration protects the HUMS from direct exposure to incident airflow during flight, thereby reducing aero-acoustic noise generation, while the access port provides a pathway for maintenance operations when the aircraft is on the ground.
Solution Approach 2:
The access port acts as an intermediary element that reconciles the conflicting requirements of noise reduction and maintenance accessibility. During flight, the port is closed to isolate the HUMS from airflow and reduce noise. During maintenance, the port is opened to allow access to HUMS components, thus mediating between the two opposing requirements.
3Ease of repair
If the structural subassembly is disassembled to access the cavity for HUMS installation, then complete access to components is achieved, but the load bearing capability is adversely affected
Solution Approach 1:
The patent introduces an access port as a segmented opening in the structural subassembly that provides access to the cavity housing HUMS components. This segmentation allows maintenance personnel to access and replace HUMS components without disassembling the entire structural subassembly, thereby preserving the structural integrity and load bearing capability of the landing gear assembly.
Solution Approach 2:
The patent extracts the HUMS components from the structural subassembly as a separate removable unit accessible through the access port. This extraction allows the HUMS to be installed and maintained as a line replaceable unit without affecting the structural subassembly's load bearing capability, as the structural component itself remains intact and assembled.
4Reliability
If a dedicated EMI shield is provided for HUMS components, then electromagnetic interference protection is improved, but the overall weight of the system increases
Solution Approach 1:
The patent merges the EMI shielding function with the existing structural subassembly by utilizing the metal chamber walls to provide electromagnetic interference protection. This integration eliminates the need for a separate dedicated EMI shield, thereby reducing the overall weight of the HUMS system while maintaining adequate EMI protection through the inherent electromagnetic shielding properties of the metal structural components.
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 solution simplifies and lightens the HUMS, allowing for easy installation and replacement without affecting the landing gear's load-bearing capability, reduces aero-acoustic noise, and facilitates retrofitting by integrating the HUMS as a line replaceable unit within the aircraft's structural components.
Implementation Method 1
the metal chamber walls can provide an electromagnetic interference (EMI) shield around the HUMS components, so as to shield other electronic aircraft systems from EMI generated by the HUMS components
Implementation Method 2
The structural subassembly can also substantially isolate the HUMS from incident airflow, which could lead to aero-acoustic noise if the HUMS components were mounted externally on the landing gear assembly
Data Source
AI summary
A health and monitoring system or “HUMS” mounted within a hollow structural subassembly of an aircraft landing gear assembly, the subassembly having an access port for access to the HUMS without requiring disassembly of the structural subassembly so as to require jacking up the aircraft.