Radome Shell Thermal Expansion Management via Sliding Fasteners
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Solution Overview
Problem
The radome assembly's shell, constructed of electrically transparent material, experiences thermal expansion and contraction, leading to significant force loads between the shell and fasteners, causing distortion and reducing the useful life of both components, and increasing operational costs due to potential weight additions from more fasteners or thicker construction.
Innovation Solution
The radome assembly features a shell with strategically positioned openings of varying dimensions and a sliding rail system, allowing for thermal expansion and contraction without applying excessive force on fasteners, using spring washers and compression angles to maintain securement while accommodating movement, thereby reducing distortion and weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If additional fasteners are employed to secure the shell to resist thermal force loads, then the shell's securement strength is improved, but the aircraft weight increases and installation costs increase
Solution Approach 1:
The patent employs a dynamic fastening system where fasteners are positioned within elongated openings that allow them to move relative to the shell along the length of the shell. This dynamic arrangement enables the fasteners to accommodate thermal expansion and contraction forces without requiring additional fasteners, thereby maintaining securement strength without increasing aircraft weight
Solution Approach 2:
The patent introduces spring washers as intermediary elements between the fasteners and the shell. These spring washers act as mediators that absorb and dissipate thermal force loads through elastic deformation, reducing the stress transmitted to both the fasteners and the shell while maintaining securement without additional weight
2Strength
If additional fasteners are employed to secure the shell, then the shell's securement strength is improved, but the installation time and labor costs increase
Solution Approach 1:
The dynamic fastening system with elongated openings allows for simpler installation since the fasteners can be positioned within the elongated openings without requiring precise alignment, reducing installation time and labor costs while maintaining securement strength
3Strength
If a thicker shell construction is employed to resist thermal force loads, then the shell's structural strength is improved, but the aircraft weight increases and operational costs increase
Solution Approach 1:
The patent uses a dynamic fastening system that accommodates thermal forces through movement and elastic deformation, allowing a thinner shell construction to resist thermal force loads effectively without the need for thicker material, thereby reducing aircraft weight and operational costs
4Stability of the object's composition
If the shell is affixed rigidly with fasteners to prevent movement, then the shell's positional stability is improved, but thermal induced distortion increases and component life decreases
Solution Approach 1:
The patent implements a dynamic fastening system where fasteners can move within elongated openings, allowing the shell to expand and contract thermally without generating excessive stress. This dynamic arrangement maintains positional stability while accommodating thermal movement, preventing distortion and extending component useful life
Solution Approach 2:
The patent changes the constraint parameters from rigid fixed positions to movable positions within elongated openings. This parameter change allows the shell to undergo thermal expansion and contraction while maintaining securement, preventing distortion and extending the useful life of the shell and fasteners
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 extends the useful life of the radome assembly and reduces operational costs by minimizing weight additions and installation complexities, while maintaining the aerodynamic and weatherproof integrity of the radar system.
Implementation Method 1
the material from which the shell is constructed experiences expansions and contractions based on the thermal expansion coefficient of the material
Data Source
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AI summary
A radome assembly of an aircraft includes a shell having an elongated shape wherein the shell defines a first opening having a diameter of a first dimension and is positioned within a first end portion of the shell. The shell defines a second opening having an elongated shape which extends along a length of the shell and has a second dimension which is greater than the first dimension. First fastener extends through the first opening and is engaged with a first surface associated with a first structural element and resists movement of the shell and the first structural element relative to one another. Second fastener extends through the second opening and is engaged with a second surface associated with the first structural element such that the shell is moveable along the length of the shell relative to the first structural element.