Flexible Radiator with Pyrolytic Graphite for Spacecraft Thermal Management
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Solution Overview
Problem
Existing radiators in spacecraft face challenges in combining structural and thermal functions, particularly when radiator temperatures are incompatible with the spacecraft structure, leading to mass, cost, and manufacturability issues, and the need for separate thermal and structural systems.
Innovation Solution
A radiator design featuring a heat conductive layer with in-plane heat conductivity of at least 500 W/mK, made from pyrolytic graphite, combined with a high emissivity heat emission layer, and a flexible laminate structure that includes a heat supply device, allowing for adaptable shape conforming to local requirements and thermal decoupling from the structural component using insulation layers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a rigid panel structure is used to provide structural function and heat transport, then structural strength and stiffness are improved, but flexibility and adaptability to different temperature requirements deteriorate
Solution Approach 1:
The radiator is divided into separate functional layers: a structural panel layer and a thermal control layer. This segmentation allows each layer to be optimized independently - the structural panel provides mechanical strength while the thermal control layer with phase change material provides thermal management flexibility, resolving the contradiction between structural rigidity and thermal adaptability
Solution Approach 2:
The invention uses composite structure combining structural panel material with phase change material layers. This composite approach enables the radiator to simultaneously provide structural support and adaptive thermal control, as the phase change material can absorb or release heat at specific temperatures independent of the structural panel's mechanical properties
2Weight of stationary object
If the radiator is integrated with the spacecraft structure to fulfill both structural and thermal functions, then mass is reduced, but temperature compatibility requirements increase
Solution Approach 1:
The phase change material is applied locally to specific areas of the structural panel where thermal management is needed. This localized approach allows the radiator to maintain structural integrity while providing thermal control only where required, reducing the temperature compatibility constraints on the entire structure
Solution Approach 2:
The phase change material enables the radiator to operate at different temperature levels by selecting materials with different melting points. This parameter change capability allows the same structural panel to support radiators operating at various temperatures without compromising structural integrity, thus reducing temperature compatibility requirements
3Area of stationary object
If deployable radiator panels are used to increase radiating surface area, then heat rejection capacity is improved, but structural rigidity imposes limitations on deployment flexibility
Solution Approach 1:
The deployable radiator is segmented into multiple panels that can be folded or extended. The phase change material is applied to each panel independently, allowing the structure to deploy to large surface areas while maintaining thermal control on each segment, thus overcoming the limitation of rigid panel deployment
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 design enhances heat transport and radiation capacity while allowing for flexible integration with spacecraft structures, improving thermal management without compromising structural integrity or increasing mass, and enabling compatibility with varying temperature requirements.
Implementation Method 1
at least one heat conductive layer (2) having an in-plane heat conductivity of at least 500 W/mK
Implementation Method 2
at least one heat emission layer (3) in contact with the heat conductive layer, wherein the emission layer has an exposed surface with an emissivity of at least 0.7
Data Source
AI summary
A radiator, comprising at least one heat conductive layer with pyrolytic graphite material and an in-plane heat conductivity of at least 500 W/m·K. The radiator further comprises at least one heat emission layer that is in contact with the heat conductive layer, wherein the emission layer has an exposed surface with an emissivity of at least 0.7. The radiator is to be used in combination with a space vehicle structure, and due to its flexible character may be conformed to the particular shapes of such structure.