Aircraft Engine Truss Using 17-4PH Steel and Adjustable Collars
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Solution Overview
Problem
Existing aircraft engine trusses are heavy, bulky, and insufficient for modern aircraft requirements due to their material limitations, requiring improved strength, weight reduction, and producibility, as well as reduced dimensional errors and enhanced adjustability for thrust angles.
Innovation Solution
The engine support truss assembly uses 17-4PH precipitation-hardened stainless steel for structural members, incorporates a machined collar with a slip plane for adjustable thrust angles, and features machined truss nodes for improved weldability and robotic welding, eliminating the need for shimming and post-processing steps.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional materials and designs are used for engine trusses, then structural strength is maintained, but weight increases and producibility decreases
Solution Approach 1:
The patent applies precipitation hardening to the 17-4PH stainless steel to fundamentally change the material's mechanical properties. This heat treatment process transforms the microstructure, dramatically increasing yield strength and ultimate tensile strength while reducing density compared to traditional aluminum alloys, thereby achieving both weight reduction and strength enhancement
Solution Approach 2:
The patent employs a hybrid material system combining 17-4PH precipitation-hardened stainless steel structural members with elastomeric vibration isolators. This composite approach integrates rigid load-bearing components with flexible vibration-damping elements, optimizing both structural performance and vibration isolation while reducing overall weight
2Strength
If traditional truss designs are used, then structural support is provided, but dimensional errors increase and adjustability decreases
Solution Approach 1:
The patent divides the truss structure into modular components with standardized interfaces and machined collars. This segmentation allows for precise machining of individual members and components, which can then be assembled with high dimensional accuracy, reducing cumulative errors and enabling easier adjustment of thrust angles through repositioning of modular elements
Solution Approach 2:
The patent incorporates preliminary machining of collars and mounting surfaces to precise tolerances before final assembly. This pre-machining ensures that critical dimensional features are established early, minimizing the need for post-assembly adjustments and shimming, and enabling more accurate thrust angle configuration
3Ease of operation
If manual assembly processes are used, then flexibility is maintained, but productivity decreases and complexity increases
Solution Approach 1:
The patent segments the truss into pre-fabricated modules with standardized connection interfaces, enabling both automated robotic welding during manufacturing and rapid manual assembly during installation. This modular approach maintains assembly flexibility while dramatically improving productivity through reduced on-site fabrication requirements
Solution Approach 2:
The patent designs universal machined collars and mounting interfaces that serve multiple functions: structural connection, alignment reference, and adjustment mechanism. This multi-functionality reduces the number of separate components and operations required, simplifying the assembly process and improving productivity without sacrificing flexibility
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 results in a lighter, stronger, and more producible engine truss with reduced dimensional errors, enabling efficient weight and space optimization, improved vibration damping, and simplified installation processes.
Implementation Method 1
The truss structure includes a plurality of structural members each including precipitation-hardened stainless steel
Implementation Method 2
The vibration isolators are configured to abut an engine for dampening vibrations transferred from the engine to the engine truss
Data Source
AI summary
An engine support truss assembly for aircraft includes a mounting plate having a front side and a back side opposite the front side, a truss structure mechanically coupled to the front side of the mounting plate, and a backup structure mechanically coupled to the back side of the mounting plate. The truss structure includes a plurality of structural members each including precipitation-hardened stainless steel. The backup structure is configured to provide mechanical support to the truss structure.