Space System Conductive Veil for ESD and Thermal Control
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Solution Overview
Problem
Existing space systems face challenges in preventing electrostatic discharge and maintaining adequate temperature during space missions, particularly with thin, lightweight structures that require insulation and conductive surfaces without adding significant weight or compromising mechanical properties.
Innovation Solution
A layered structure comprising a conductive veil or nonwoven with a non-conductive sheet, where the conductive veil is embedded in a matrix and provides adjustable electrical surface conductivity, reducing electrostatic discharge and serving as a heating element to prevent extreme low temperatures, while maintaining minimal weight and mechanical integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conductive support structure is used, then electrostatic discharge requirements are fulfilled, but additional insulation layers are needed between the photovoltaic assembly and the structure
Solution Approach 1:
The patent resolves this contradiction by applying local quality - the support structure has conductive properties only where needed (rear surface) and non-conductive properties where insulation is needed (front surface). This eliminates the need for additional insulation layers between the photovoltaic assembly and support structure, as the front surface itself provides the necessary insulation while the rear surface handles electrostatic discharge.
Solution Approach 2:
The patent merges multiple functions into a single support structure component. The support structure simultaneously provides mechanical support, thermal insulation (front surface), and electrostatic discharge protection (rear surface). This integration eliminates the need for separate insulation layers and simplifies the overall structure while fulfilling all requirements.
2Strength
If a rigid sandwich panel structure is used, then structural strength is provided, but significant mass is added to the solar array
Solution Approach 1:
The patent replaces the traditional rigid sandwich panel structure with a thin polymer foam support structure. This foam material provides the necessary structural strength and rigidity while being significantly lighter than conventional sandwich panels. The foam's cellular structure gives it high strength-to-weight ratio, allowing the solar array to maintain structural integrity without adding excessive mass.
Solution Approach 2:
The patent uses composite materials by incorporating conductive particles or fibers into the polymer foam matrix. This creates a composite structure that combines the lightweight, insulating properties of the polymer foam with the electrostatic discharge properties of the conductive additives, achieving multiple functions in a single lightweight component.
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
The solution effectively reduces electrostatic discharge and prevents temperature drops in space systems, ensuring the structural integrity and efficiency of components like solar arrays by providing a lightweight, conductive layer that can be heated to maintain operational temperatures without increasing the overall system weight.
Implementation Method 1
the structure does not fulfill electrostatic discharge requirements concerning the surface conductivity
Implementation Method 2
the conductive veil or nonwoven may be used for heating the structure or components during long eclipses or deep space missions to prevent extremely low temperatures
Data Source
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AI summary
We generally describe a space system comprising a layered structure on an outer surface of the space system, the layered structure comprising: a conductive veil or nonwoven comprising conductive fibers; and a non-conductive sheet arranged on a surface of the conductive veil or nonwoven.