Satellite Attitude-Based Thermal Control for Small Spacecraft
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Solution Overview
Problem
Conventional thermal control systems for spacecraft are challenging for small satellites due to mass, surface area, volume, and power constraints, limiting the applicability of passive and active thermal management techniques.
Innovation Solution
A satellite with a radiative surface and an attitude determination and control system (ADCS) that adjusts its orientation relative to the sun to control thermal radiation heat transfer, using the radiative surface to either emit or absorb heat actively, thereby managing temperature without additional components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional passive thermal control systems use body panel radiators to dissipate heat, then thermal control function is provided, but satellite size increases due to required radiator area
Solution Approach 1:
The patent applies dynamics by making the radiator panel deployable and reconfigurable. The radiator can be extended or folded based on thermal control needs, allowing the same physical structure to provide different surface areas when required. This resolves the contradiction by enabling the satellite to have a compact form factor while still providing sufficient radiator area when needed for thermal control.
Solution Approach 2:
The radiator system is segmented into deployable sections that can be extended or folded independently. This allows the radiator area to be dynamically adjusted without increasing the permanent satellite volume, resolving the contradiction between providing sufficient thermal control surface area and maintaining a compact satellite design.
2Temperature
If deployable radiators are used for small spacecraft, then thermal control is achieved, but implementation becomes challenging due to volumetric constraints
Solution Approach 1:
The radiator panel serves multiple functions: it acts as a thermal control radiator, a structural component, and a deployable mechanism. By making the radiator multi-functional and integrating it with the satellite structure, the patent reduces the complexity of implementing separate deployable radiator systems while still achieving thermal control for small spacecraft.
3Temperature
If active thermal control methods are used, then tighter temperature control is achieved, but power, mass and volume requirements increase
Solution Approach 1:
The patent applies self-service by using the satellite's own motion and orientation control to manage thermal loads. The satellite uses its attitude control system to orient radiating surfaces toward or away from heat sources, and utilizes its own operational cycles (such as communication cycles) to modulate thermal loads. This eliminates the need for separate active thermal control systems, achieving tight temperature control without the additional power and mass requirements.
Solution Approach 2:
The patent merges thermal control functions with existing satellite systems, particularly the attitude control and communication systems. By combining the thermal management function with these existing systems, the patent achieves active thermal control capabilities without adding separate powered equipment, thus avoiding the increased power, mass and volume requirements.
4Temperature
If active thermal control devices are integrated into small satellites, then temperature control is improved, but integration becomes difficult due to mass and volume constraints
Solution Approach 1:
The satellite performs thermal control using its own existing systems (attitude control, communication cycles) without requiring separate active thermal control devices. This self-service approach eliminates the need to integrate additional mass-consuming components while still achieving effective temperature control.
Solution Approach 2:
Existing satellite components are made multi-functional to perform both their primary functions and thermal control functions. For example, the attitude control system is used for both orientation and thermal management, and communication cycles are used for both data transmission and thermal load modulation. This multi-functionality eliminates the need for separate thermal control devices, resolving the mass constraint.
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 approach provides active thermal control for small satellites, reducing costs and integration time while meeting temperature requirements, allowing for smaller satellite designs and reducing power consumption.
Implementation Method 1
a satellite body including at least one radiative surface configured to emit satellite heat to space
Implementation Method 2
an ADCS system configured to change the orientation of the satellite with respect to the sun between a first position in which the radiative surface points away from the sun and a second position in which the radiative surface is exposed to the sun
Data Source
AI summary
The invention relates to a satellite comprising: a satellite body including at least one radiative surface configured to emit satellite heat to space; and an attitude determination and control ‘ADCS’ system for controlling an orientation of the satellite travelling in orbit around Earth, wherein the ADCS system is configured to change the orientation of the satellite with respect to the sun between a first position in which the radiative surface points away from the sun and a second position in which the radiative surface is exposed to the sun. The invention further relates to a method of controlling thermal radiation heat transfer of a satellite.