Capsulation Satellite Module Thermal Control
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Solution Overview
Problem
Satellites and space probes face extreme temperature variations in outer space, leading to thermal cycling stress and equipment failure, with existing thermal control systems being cumbersome, expensive, and inefficient in terms of space, weight, and power usage.
Innovation Solution
A hermetically sealed capsulation satellite module with a continuous sidewall and dual gas chambers connected to a sealed inner cavity, utilizing fan plate assemblies to maintain terrestrial atmospheric pressure and temperature, with fan units circulating air between the cavity and gas chambers to regulate temperature.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional thermal control devices are used to maintain temperature in space satellites, then temperature stability is improved, but device complexity, weight, and power consumption increase
Solution Approach 1:
The patent changes the physical state of the thermal control system by using gas-filled chambers instead of solid-state thermal control devices. The gas chambers can be pressurized or evacuated to control thermal properties, allowing temperature stabilization without complex mechanical thermal control systems. This parameter change from solid to gas phase enables simpler, lighter thermal management.
Solution Approach 2:
The patent uses an inert gas environment within the sealed chambers to create a stable thermal environment for the payload. The gas-filled chambers act as thermal buffers that isolate the payload from extreme space temperature variations, providing passive thermal control without requiring active heating or cooling systems.
2Temperature
If conventional thermal control devices are used in space satellites, then temperature stability is improved, but weight increases
Solution Approach 1:
The patent transitions from heavy solid-state thermal control components to lightweight gas-filled chambers. By changing the medium from solid to gas, the system achieves comparable thermal control performance with significantly reduced weight, as gases have much lower density and can be contained in thin-walled structures.
Solution Approach 2:
The patent replaces mechanical thermal control devices (such as heaters, coolers, and thermal switches) with a gas-based passive thermal control system. This substitution eliminates the need for heavy mechanical components while maintaining temperature stability through the thermal properties of the gas medium.
3Temperature
If conventional thermal control devices are used in space satellites, then temperature stability is improved, but power consumption increases
Solution Approach 1:
The gas-filled chambers provide self-regulating thermal control without requiring external power input. The gas medium naturally responds to temperature changes through expansion and contraction, creating a passive thermal buffer that stabilizes payload temperature without consuming electrical power, unlike active thermal control systems that require heaters or coolers.
Solution Approach 2:
The patent replaces electrically-powered thermal control devices with a mechanically passive gas-based system. This substitution eliminates the need for electrical power to drive thermal control mechanisms, as the gas chambers automatically adjust to temperature variations through physical expansion and contraction.
4Reliability
If conventional satellite modules are used for space exploration, then proven reliability is achieved, but cost and complexity increase
Solution Approach 1:
The patent divides the satellite module into separate sealed chambers, each with its own gas-filled thermal control environment. This segmentation allows independent thermal management of different payload components, improving reliability by isolating thermal stresses while maintaining overall system simplicity through modular design.
Solution Approach 2:
The patent creates inert gas environments within sealed chambers to protect sensitive equipment from both thermal extremes and potential contamination. This inert atmosphere approach provides a simple yet effective method for enhancing equipment reliability without adding complex protection systems.
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 provides a compact, lightweight, low-power thermal control system that maintains a stable terrestrial environment within the satellite module, reducing thermal cycling stress and enhancing equipment longevity while offering significant power savings.
Implementation Method 1
Each of the first gas chamber and the second gas chamber is fluidly connected to the sealed inner cavity and to each other through the sealed inner cavity to maintain predetermined pressure and temperature within the cavity
Implementation Method 2
fan units circulating air between the cavity and gas chambers to regulate temperature
Data Source
AI summary
A capsulation satellite module for transferring a payload by an earth-launch vehicle to an outer space. The capsulation satellite module comprises a casing defining a hermetically sealed inner cavity therewithin. The casing includes a continuous sidewall and first and second cover assemblies mounted to axially opposite sides of the sidewall so as to delimit the hermetically sealed inner cavity within the casing. The first cover assembly defines a first gas chamber therein extending over the inner cavity of the casing. The second cover assembly defines a second gas chamber therein extending over the inner cavity of the casing. Each of the first gas chamber and the second gas chamber are fluidly connected to the sealed inner cavity and to each other through the sealed inner cavity to maintain predetermined pressure and temperature within the cavity.