Flexible Radiative Fin With Self-Deployment for Spacecraft Cooling
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Solution Overview
Problem
Current deployable radiators for satellites are complex, costly, and heavy due to the need for mechanical actuation and 2-phase heat transport systems, which are not adaptable to the increasing demand for efficient cooling in smaller, constellation-based satellites with variable heat rejection needs.
Innovation Solution
A flexible radiative fin using pyrolytic graphite sheets and a heat emission layer, self-deploying without mechanical actuators, utilizing the torque of a flexible rod for deployment and folding, and integrated with solar array wings for activation, simplifying design and reducing weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional deployable radiators with mechanical actuators and 2-phase heat transport systems are used, then heat rejection capability is maximized, but device complexity, weight, and cost increase significantly
Solution Approach 1:
The patent removes mechanical actuators and complex 2-phase heat transport systems from the radiator structure, retaining only the essential heat rejection function through a simplified single-phase heat pipe system integrated directly into the flexible laminate structure
Solution Approach 2:
The flexible radiative fin uses its own flexibility and elastic memory to automatically deploy and retract without external mechanical actuators, and uses integrated heat pipes to self-transport heat from the satellite body to the radiative surface
2Strength
If rigid metallic sandwich panels with honeycomb structure are used for deployable radiators, then structural strength and heat rejection are improved, but weight and device complexity increase
Solution Approach 1:
The patent replaces rigid metallic sandwich panels with a flexible radiative laminate structure consisting of thin layers (support layer, heat conductive layer, heat emission layer) that can bend and deploy without requiring heavy internal honeycomb structures
Solution Approach 2:
The radiator uses a composite laminate structure combining different materials (support layer material, heat conductive material, heat emission material) to achieve both structural integrity and thermal performance in a lightweight flexible form
3Power
If 2-phase heat transport systems with large diameter pipes are used, then heat transport capacity is maximized, but weight and device complexity increase due to thick walls and high pressure requirements
Solution Approach 1:
The patent replaces complex 2-phase heat transport systems with high-pressure pipes and mechanical actuators with a simpler single-phase heat pipe system that uses capillary action and phase change within the heat pipe structure itself for heat transport
Solution Approach 2:
The heat pipe system is integrated directly into the flexible radiative laminate structure, merging the heat transport function with the radiative surface structure rather than using separate heavy piping systems
4Reliability
If deployable radiators are designed for maximal cooling capacity, then heat rejection is improved, but the radiator becomes heavier and more costly
Solution Approach 1:
The patent creates a dynamically adaptable radiator that can adjust its deployed area based on thermal demands through the flexible nature of the laminate and controlled deployment/retraction mechanisms, allowing the same structure to serve different cooling requirements
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 flexible radiative fin provides efficient heat dissipation, is cheaper and lighter, and offers adaptable cooling capacity without the need for complex mechanical systems, suitable for satellites with varying thermal demands.
Implementation Method 1
a flexible radiative laminate (20), said flexible radiative laminate comprising at least one pyrolytic graphite sheet (21) serving as a heat transporting layer
Implementation Method 2
at least one heat emission layer (22), in contact with one pyrolytic graphite sheet (21) and preferably adhered to the latter by a layer of adhesive material (23)
Implementation Method 3
a flexible rod (30), which extends from the end fitting (10) on a side of the radiative laminate (20)
Data Source
Figure 1
Figure 2a~2b
Figure 3~4
AI summary
The invention proposes a radiative fin (1) for a spacecraft, comprising: - an end fitting (10) of heat conductive material, adapted to be mounted on the spacecraft, - a flexible radiative laminate (20), connected to the end fitting at one end and having an opposite free end, and comprising : ∘ at least one pyrolytic graphite sheet, and ∘ at least one heat emission layer in contact with the pyrolythic graphite sheet on at least part of the surface of the pyrolythic graphite sheet, and - a flexible rod (30), extending from the end fitting (10) along at least part of a side of the flexible radiative laminate (20) and being affixed to the latter, wherein the flexible rod (30) is adapted to occupy a folded position and a deployed position and to exert, while in the folded position, a deployment torque adapted to bring the flexible rod back to the deployed position.