Stamped Aluminum Satellite Shell With Integrated Stiffeners
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Solution Overview
Problem
Conventional satellites using aluminum honeycomb cores for load-bearing structures are expensive and difficult to manufacture, requiring specialized interface structures for payload fixation, and lack design predictability.
Innovation Solution
Manufacture space vehicles with outer shells made from stamped aluminum panels, incorporating stiffeners and onboard equipment components directly fixed to the panels, eliminating the need for honeycomb cores and allowing for optimized design and cost-effective production.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If aluminum honeycomb cores are used for load-bearing structures, then high stiffness-to-density ratio is achieved, but manufacturing complexity and cost increase
Solution Approach 1:
The patent extracts and eliminates the honeycomb core from the sandwich panel structure, retaining only the outer skin panels. This removes the complex internal honeycomb structure while maintaining structural integrity through alternative means (proper panel thickness and stiffening), thereby simplifying manufacturing without sacrificing the stiffness-to-density advantage
Solution Approach 2:
The patent replaces expensive, difficult-to-manufacture honeycomb panels with simpler, more cost-effective solid aluminum panels. The solid panels achieve sufficient structural performance through appropriate thickness selection and stiffening, providing a more economical solution that maintains the essential load-bearing function
2Weight of moving object
If honeycomb panels are used, then lightweight structure is achieved, but design predictability decreases
Solution Approach 1:
The patent changes the structural parameter from hollow honeycomb cores to solid panels with controlled thickness. This parameter change simplifies the structural model, making it more predictable and easier to analyze. The solid panel approach provides more straightforward stress distribution and failure mode prediction compared to the complex honeycomb structure
3Strength
If honeycomb panels are used, then load-bearing capacity is achieved, but ease of manufacture decreases
Solution Approach 1:
The patent removes the difficult-to-manufacture honeycomb core from the structure, retaining only the essential load-bearing skin panels. This extraction eliminates the need for complex honeycomb fabrication, core bonding, and interface structure design, while maintaining adequate load-bearing capacity through proper panel specification
Solution Approach 2:
The solid panels serve multiple functions simultaneously: they provide the outer skin, the load-bearing structure, and the mounting surface for payload elements. This multi-functionality eliminates the need for separate honeycomb cores and specialized interface structures, greatly simplifying manufacturing
Data Source
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AI summary
Ae methhod includes providing a quantity of sheet metal, press-forming a first panel from the sheet metal to form a first stamped panel, press-forming a second panel from the sheet metal to form a second stamped panel, fixing at least one stiffener to the first stamped panel such that the stiffener extends across a width of the first panel, where a first end of the stiffener is attached to the first stamped panel at a first fixation location, and where a second end of the stiffener is attached to the first stamped panel at a second fixation location, fixing at least one onboard equipment component to the first stamped panel, where at least one of the at least one onboard equipment component is fixed to the stiffener, sealing the first panel to the second panel to form a space vehicle.