Spacecraft Thermal Platform with Temperature Responsive Bypass
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Solution Overview
Problem
Current spacecraft thermal control systems are complex, heavy, expensive, and inefficient, particularly for small spacecraft, and lack flexibility and precise temperature control, as they rely on variable conductance heat pipes and active heating systems that require significant power and are not adaptable to different mission scenarios.
Innovation Solution
A modular thermal platform with a two-phase loop system, including a bypass line, heat flow regulator, and thermal insulation, which uses capillary action for fluid circulation and bypasses heat flow to manage temperature, allowing for independent operation and efficient heat transfer over long distances without additional systems or power consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If variable conductance heat pipes and active heating systems are used for thermal control, then temperature control capability is improved, but system complexity, weight, and power consumption increase
Solution Approach 1:
The patent extracts the active control elements (heaters, complex sensors, and control systems) from the thermal management architecture, retaining only the passive two-phase loop system with bypass. This eliminates the need for power-consuming active heating systems while maintaining temperature control through the bypass mechanism that diverts heat flow around the radiator when temperature drops occur.
Solution Approach 2:
The thermal control system operates autonomously using passive two-phase thermodynamic cycles. The bypass mechanism automatically activates when temperature drops, diverting heat flow without requiring external power or control systems. The system self-regulates temperature through the inherent thermodynamic properties of the working fluid and the bypass geometry, eliminating the need for active heating systems.
2Temperature
If variable conductance heat pipes are used for thermal control, then temperature stabilization is improved, but weight and cost increase significantly
Solution Approach 1:
The patent replaces expensive, heavy variable conductance heat pipes with a simpler, lighter two-phase loop system with bypass. The bypass mechanism uses basic thermal conduction paths and geometry rather than complex adjustable conductance structures, significantly reducing weight and cost while achieving comparable temperature stabilization through passive thermodynamic control.
3Power
If additional thermal control systems are added to manage heat transfer, then heat transfer efficiency is improved, but power consumption increases
Solution Approach 1:
The patent replaces active mechanical thermal control systems (pumps, valves, heaters) with a passive two-phase thermodynamic system. Heat transfer is achieved through phase change of the working fluid and natural convection, eliminating the need for powered components. The bypass mechanism uses passive thermal conduction paths to manage heat flow without requiring any power input.
4Adaptability or versatility
If modular thermal platform is used, then adaptability to different missions is improved, but design and integration complexity increases
Solution Approach 1:
The patent implements a modular thermal platform where the spacecraft is divided into independent thermal zones, each with its own two-phase loop system and bypass mechanism. This segmentation allows each module to be independently designed, tested, and integrated, reducing overall system complexity while providing adaptability to different mission requirements through selective module configuration.
Solution Approach 2:
The modular thermal platform uses standardized two-phase loop systems with bypass mechanisms that can be universally applied across different spacecraft and mission types. The same basic module design serves multiple thermal control functions and can be scaled or configured for different power levels and temperature requirements, reducing design complexity through reuse of proven architectures.
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 modular platform provides flexible and efficient thermal management, reducing design and testing time and costs, enabling precise temperature control and high heat load management across various space missions and orbits, with the ability to handle up to 10 kW of power and operate in any spacecraft orientation.
Implementation Method 1
uses capillary action for fluid circulation
Implementation Method 2
thermal insulation system
Implementation Method 3
heat loads must be rejected to deep space that works as a thermal sink. Since no matter links this sink and the spacecraft, this rejection is made by thermal radiation
Data Source
AI summary
A thermal module for use on a spacecraft to control thermal loads coming from a heat source is disclosed. The thermal module includes a two-phase loop system and a heat rejection system. The two-phase loop system includes a thermal collector, a heat flow regulator, a by-pass line, and a condenser. The condenser and the heat rejection system are thermally coupled, such that the heat flow regulator redirects part of the thermal loads from the heat source to the condenser, from which the heat rejection system directs said thermal loads to a heat sink. The temperature of the heat source is regulated by bypassing another part of the thermal loads back to the thermal collector through the by-pass line in a proportional manner, to avoid overcooling the heat source. The heat rejection system is designed based on the hottest possible conditions for the spacecraft mission.