A satellite system
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Solution Overview
Problem
Existing satellite systems using superconducting electromagnets for position control face challenges in effective cooling and thermal management, particularly in space environments, leading to increased bulkiness and mass due to the need for cryogenic cooling systems like liquid nitrogen, which complicates satellite design and reduces maneuverability.
Innovation Solution
A satellite design incorporating a superconducting magnet control system with a cryocooler thermally coupled to a cooling element for conduction cooling, allowing the superconducting electromagnet to be cooled efficiently without the need for bulky cryogenic fluids, thereby reducing mass and volume while maintaining the electromagnet in a superconducting state.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If liquid nitrogen is used as an outer jacket to prevent helium boiling, then the cooling effectiveness is improved, but the satellite mass and volume increase significantly
Solution Approach 1:
The invention extracts and eliminates the liquid nitrogen outer jacket from the cooling system, replacing it with a passive radiative cooling approach that uses the space environment directly, thereby removing the unnecessary mass while maintaining cooling effectiveness
Solution Approach 2:
The invention introduces a radiative cooler as an intermediary component that mediates between the helium coolant and the space environment, enabling efficient heat rejection through thermal radiation without requiring a bulky liquid nitrogen jacket
2Temperature
If liquid nitrogen outer jacket is used to cool the electromagnet, then the superconducting state is maintained, but the device complexity increases
Solution Approach 1:
The invention removes the complex active cooling infrastructure (liquid nitrogen jacket, pumps, valves, and control systems) and replaces it with a passive radiative cooling system that maintains the superconducting temperature through simple thermal management components
Solution Approach 2:
The radiative cooler operates autonomously using the space environment's low temperature and thermal radiation principles, eliminating the need for active cooling systems and complex control mechanisms while maintaining the required temperature
3Temperature
If conventional cooling methods are used, then the electromagnet can be cooled, but the satellite volume and bulkiness increase
Solution Approach 1:
The invention extracts and eliminates the bulky liquid nitrogen storage and circulation infrastructure, replacing it with a compact passive radiative cooler that achieves the same cooling function with minimal volume
Solution Approach 2:
The invention transitions from volumetric cooling (liquid nitrogen storage and circulation) to surface-based radiative cooling, utilizing the surface area of the radiative cooler to reject heat directly to space, thereby dramatically reducing the required volume
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 enables efficient cooling of superconducting electromagnets in satellites, reducing mass and volume, enhancing maneuverability, and providing a reliable, low-maintenance cooling solution suitable for space environments.
Implementation Method 1
the cryocooler is thermally coupled to the cooling element to cool the superconducting electromagnet or at least one or more components thereof through the cooling element by conduction cooling alone
Implementation Method 2
in a superconducting state the wires of such electromagnets have zero electrical resistance and therefore can conduct much larger electric currents than ordinary wires, creating an intense magnetic field
Implementation Method 3
a superconducting magnet control system mounted to or within at least a portion of the chassis for position control of the satellite
Data Source
Figure 1~2
Figure 3
Figure 4~5
AI summary
A novel cooling system for a superconducting electromagnet (740) that is suitable for use in satellite (700), or at least one or more components of the electromagnet (740) is disclosed. A satellite (700) and electromagnetic control system (705) for position control of such a satellite (700) are also disclosed. In one embodiment, the superconducting magnet control system (705) comprises at least one superconducting electromagnet (740) with at least one cooling element and at least one cryocooler (735). The cryocooler (735) is thermally coupled with the cooling element thereby enabling cooling of the superconducting electromagnet (740) or at least one or more components thereof through the cooling element solely by conduction cooling.