Thermal Control Panel for Spacecraft Heat Loss Reduction
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Solution Overview
Problem
Spacecraft with flexible solar arrays face battery depletion during the upper stage launch phase and transfer orbit due to inability to generate solar energy in the collapsed configuration, leading to potential loss of the spacecraft as traditional thermal shields are costly and weight-added, and not all solar panel arrays can generate energy in this configuration.
Innovation Solution
A thermal control system comprising an extensible member and a thermal control panel with differing emissivity and absorptivity sides, which can collect and re-radiate solar energy to minimize heat loss and maintain spacecraft temperature without draining battery power, suitable for both flexible and rigid solar arrays.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional thermal shields are attached to the spacecraft solar array or radiator panels, then radiative heat loss is reduced, but the spacecraft weight increases and cost increases
Solution Approach 1:
The thermal control panel uses the spacecraft's own solar array to generate electrical power that directly drives onboard heaters, eliminating the need for external thermal shields. The system serves itself by converting solar energy to electrical energy to maintain thermal balance, reducing both weight and cost while preventing battery depletion during critical phases.
Solution Approach 2:
The invention changes the operational parameters of the solar array by controlling it to face the sun during the collapsed configuration phase, enabling energy generation when traditionally the array would be powerless. This parameter change (orientation control) allows the solar array to produce electrical energy for heating without requiring additional thermal shield components.
2Temperature
If traditional thermal shields are used to prevent heat loss, then spacecraft temperature is maintained, but battery power is depleted due to inability to generate solar energy in collapsed configuration
Solution Approach 1:
The thermal control system enables the solar array to serve dual purposes: maintaining thermal balance through electrical power generation for heaters, and eliminating the need for external thermal shields. The solar array controls its own orientation to maximize energy generation during the collapsed configuration, creating a self-sustaining system that prevents battery depletion.
Solution Approach 2:
The solar array is made multi-functional by controlling it to perform both its primary function of generating electrical energy and a secondary function of thermal control during the collapsed configuration. By facing the sun in the collapsed state, the array generates power that directly supports heating requirements, eliminating the need for separate thermal management systems and preventing battery exhaustion.
3Use of energy by moving object
If solar energy generation is performed in collapsed configuration by facing solar array outboard, then solar energy is collected, but this is only possible for spacecraft using rigid solar panel arrays
Solution Approach 1:
The invention applies dynamic control to the solar array, enabling it to actively change its orientation and face the sun during the collapsed configuration. This dynamic capability allows both rigid and flexible solar arrays to optimize their energy generation, transforming a static limitation into a controllable parameter that adapts to mission requirements regardless of array type.
Solution Approach 2:
The control mechanism is designed to be universal, working with both rigid and flexible solar array types. By implementing a control system that manages the solar array's orientation rather than relying on fixed structural properties, the invention makes solar energy generation in collapsed configuration accessible to diverse spacecraft designs, enhancing adaptability across different platform types.
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 system effectively reduces heat loss and maintains spacecraft temperature, extending battery life and eliminating the need for onboard heaters, thereby preventing battery depletion and ensuring spacecraft functionality during critical phases.
Implementation Method 1
the panel can be configured to absorb incident solar energy and emit heat toward the exposed area thereby adding heat to the spacecraft side
Implementation Method 2
the panel can be configured to absorb incident solar energy and emit heat toward the exposed area
Implementation Method 3
the first side can have an emissivity that is less than the emissivity of the second side... the panel can also restrict heat loss from the panel to the environment
Data Source
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AI summary
A system and apparatus are provided for preventing heat loss in a spacecraft during the upper stage launch phase and transfer orbit. A thermal control panel can be provided that can be positioned adjacent to exposed areas of radiator panels on the spacecraft in a collapsed configuration. The outer surface of the panel can have a high absorptivity, and the inner surface can have a high emissivity. During upper stage launch phase and transfer orbit, the panel can tend to emit heat toward the radiator panels on an inboard side of the spacecraft, thus reducing heat loss from the radiator panels to reduce the need for onboard electronic heaters and thereby preserve battery power for other onboard systems.