Spacecraft Battery Thermal Management via East-West Radiator Repositioning
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Solution Overview
Problem
Conventional spacecraft battery thermal management systems constrain payload and bus equipment capacity by requiring significant radiating surface area for batteries, which reduces available space on North and South facing sides of spacecraft.
Innovation Solution
The use of heat pipes thermally couples radiator panels to spacecraft batteries, allowing these panels to be positioned on East and West sides, enabling heat dissipation while freeing up North and South sides for additional payload and bus equipment, and incorporating variable conductance heat pipes to control heat transfer based on solar exposure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If radiator panels are conductively bonded to batteries and positioned on North or South facing sides, then battery thermal management is achieved, but available area for payload and bus equipment on North and South facing sides is significantly reduced
Solution Approach 1:
The patent repositions radiator panels from traditional North/South facing sides to East/West facing sides of the spacecraft, utilizing underutilized surface areas. This dimensional repositioning allows battery thermal management to occur without competing for prime real estate on North/South faces, thereby resolving the space conflict while maintaining effective heat dissipation to space.
Solution Approach 2:
The thermal management system is segmented into multiple independent radiator panels that can be distributed across different spacecraft surfaces (East and West faces). This segmentation allows heat dissipation functions to be distributed rather than concentrated, freeing up North/South areas for payload equipment while maintaining adequate thermal control through multiple distributed radiating surfaces.
2Temperature
If larger radiating surface area is provided for batteries, then battery temperature control is improved, but overall payload capabilities of the spacecraft are constrained
Solution Approach 1:
The patent exploits the East/West facing surfaces of the spacecraft as additional thermal management real estate. By positioning radiator panels on these previously underutilized surfaces, the system provides adequate radiating area for battery thermal control without encroaching on the North/South facing areas that are critical for payload equipment deployment, thus maintaining full payload capabilities.
Solution Approach 2:
The patent applies thermal management resources (radiator panels) locally to the East/West facing surfaces where they are most needed for heat dissipation, rather than uniformly distributing them across all spacecraft surfaces. This localized application optimizes the use of available surface area, providing adequate thermal control for batteries while preserving North/South areas for high-value payload equipment.
3Area of stationary object
If radiator panels are positioned on East and West facing sides, then area on North and South facing sides is freed for payload and bus equipment, but heat transfer control must be optimized to account for solar exposure variations
Solution Approach 1:
The patent leverages the periodic nature of spacecraft orbital exposure to solar radiation. By positioning radiator panels on East/West facing sides, the system naturally experiences periodic solar exposure as the spacecraft orbits, allowing thermal management to adapt to varying heat loads without complex active control. The periodic solar illumination patterns are utilized to enhance heat dissipation during appropriate orbital phases.
Solution Approach 2:
The patent employs variable conductance heat pipes that can dynamically adjust their thermal conductivity parameter in response to changing thermal conditions. This allows the heat transfer rate between batteries and radiator panels to be modulated based on real-time thermal demands and solar exposure conditions, simplifying overall system control while maintaining effective thermal management across varying operational parameters.
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 configuration increases payload and bus equipment capacity by optimizing thermal management, reducing the need for heaters during charging, and enhancing energy capture from solar cells on radiator panels.
Implementation Method 1
multiple radiator panels are thermally coupled to a battery using heat pipes
Implementation Method 2
Excess heat generated by the batteries is dissipated using radiator panels thermally coupled to the batteries
Implementation Method 3
incorporating variable conductance heat pipes to control heat transfer based on solar exposure
Data Source
AI summary
A spacecraft battery thermal management system is provided that includes a battery, a first radiator panel and a second radiator panel. A first face of the first radiator panel is arranged to face a first direction and a first face of the second radiator panel is arranged to face a second direction opposite the first direction. A first heat pipe thermally couples the battery and the first radiator panel and is configured to control the transfer of heat between the battery and the first radiator panel. A second heat pipe thermally couples the battery and the second radiator panel and is configured to control the transfer of heat between the battery and the second radiator panel. Solar cells are optionally arranged on the faces of the first and/or second radiator panels.