Pressurized Space Vehicle Compartment Thermal Management
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Solution Overview
Problem
Current space vehicle technologies are prohibitively expensive and time-consuming to develop due to the need for custom designs optimized for specific missions, and they face challenges with thermal management in extreme temperature and vacuum environments, leading to high costs and reduced reliability.
Innovation Solution
A mission-agnostic space vehicle platform with a pressurized structure and thermal management system using a thermal working fluid for convective heat transfer, along with central mounting configurations and semi-passive thermal management, to reduce costs and increase payload capacity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If custom designs optimized for specific missions are used, then mission performance is improved, but development cost and time increase significantly
Solution Approach 1:
The patent implements a universal spacecraft bus platform that can accommodate multiple different payloads and mission profiles. The standardized platform includes common subsystems (power, propulsion, thermal management) that serve multiple missions, while allowing payload-specific customization. This resolves the contradiction by enabling one design to serve multiple missions rather than requiring custom designs for each mission.
Solution Approach 2:
The spacecraft is divided into modular segments: a standardized bus platform and interchangeable payload modules. This segmentation allows the core platform to be developed once and reused, while only the payload segments need customization for different missions, reducing overall development cost and time while maintaining mission-specific performance.
2Device complexity
If components are mounted directly to externally facing panels, then structural simplicity is improved, but thermal management becomes problematic in extreme temperature environments
Solution Approach 1:
The patent introduces thermal management panels as intermediary components between the spacecraft structure and mounted components. These panels act as thermal mediators that can be actively controlled to maintain stable temperatures for sensitive electronics, resolving the contradiction by adding thermal management capability without requiring direct mounting to externally facing panels.
Solution Approach 2:
Different regions of the spacecraft structure are given different thermal properties. Externally facing panels are designed with specific thermal characteristics, while internal mounting surfaces are provided with active thermal control. This local differentiation allows structural simplicity externally while providing thermally stable environments internally where components are mounted.
3Temperature
If heavy and costly heat transfer systems are used, then thermal management performance is improved, but payload capacity and cost-effectiveness decrease
Solution Approach 1:
The thermal management system utilizes the spacecraft's own operational heat and orbital environment to provide cooling. Waste heat from electronics is directed to radiator panels that reject heat to space, and the natural temperature differential between sunlit and shaded portions of the spacecraft is exploited for passive thermal control. This self-service approach provides effective thermal management without requiring heavy active cooling systems.
Solution Approach 2:
The patent converts the harmful effect of waste heat generation into a beneficial thermal management resource. Heat rejected by electronics is captured and redirected to radiator surfaces, and the extreme temperature environment of space is utilized as a heat sink. This transforms the thermal challenge into an asset, providing effective cooling without additional weight.
4Reliability
If pressurization is applied to the entire payload compartment, then component protection in vacuum environment is improved, but system complexity and mass increase
Solution Approach 1:
Rather than pressurizing the entire payload compartment, the patent applies pressurization locally only to specific sensitive components that require protected environments. This selective pressurization reduces the mass and complexity of pressure vessels and life support systems while still providing necessary protection to critical electronics and mechanisms.
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 enables cost-effective and efficient thermal management, reducing the need for heavy and costly heat transfer systems, allowing for a versatile platform that can operate across various mission profiles without redesign, thereby lowering development time and costs.
Implementation Method 1
a thermal fluid is provided in the pressurized structure, the thermal fluid enabling convective heat transfer between the component mounted on the internal mounting structure and the interior surfaces of the pressurized structure
Data Source
AI summary
A compartment for a space vehicle includes a pressurized structure having a structural wall, the structural wall having interior surfaces facing an interior of the compartment and exterior surfaces exposed to an external environment. An internal mounting structure for mounting a component is provided within the compartment, and mounting features support the internal mounting structure from the pressurized structure. The internal mounting structure is spaced away from the interior surfaces of the pressurized structure, and a thermal fluid is provided in the pressurized structure. The thermal fluid enables convective heat transfer between the component mounted on the internal mounting structure and the interior surfaces of the pressurized structure.