Heat Pipe Cooling Structure for Superconducting MPD Thruster Electrodes
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Solution Overview
Problem
Superconducting magneto plasma dynamic thrusters face electrode ablation due to high-temperature plasma, leading to safety concerns and complexity with traditional active water cooling systems, which are not suitable for deep space applications.
Innovation Solution
A cylindrical heat pipe cooling structure with cathode and anode cooling mechanisms, including capillary loop heat pipes and heat dissipation fins, that utilize evaporation and condensation sections for passive heat dissipation without requiring additional power systems, allowing for efficient cooling of the thruster components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional active water cooling device is used, then cooling effect is achieved, but system complexity increases and safety decreases
Solution Approach 1:
The heat pipe cooling structure utilizes the phase change properties of the working fluid to automatically transport heat from the electrode to the heat dissipation fin without requiring external power or control systems. The system self-regulates temperature through natural convection and phase change, eliminating the need for pumps, valves, and control electronics that would increase system complexity.
Solution Approach 2:
The patent replaces the mechanical active water cooling system (pumps, pipes, valves) with a passive heat pipe system that uses phase change and capillary action to achieve the same cooling function. This substitution eliminates moving parts and mechanical complexity while maintaining effective heat removal from the electrode.
2Reliability
If heat pipe cooling structure is used, then system complexity is reduced and safety is improved, but cooling efficiency must be maintained
Solution Approach 1:
The heat pipe utilizes phase transitions of the working fluid (evaporation at the heating end, condensation at the cooling end) to efficiently transport heat. The phase change process absorbs and releases large amounts of latent heat, enabling high heat transfer efficiency without requiring complex active cooling systems. This phase change mechanism is the core of the heat pipe's ability to maintain cooling efficiency passively.
Solution Approach 2:
The patent extends the heat pipe structure into the third dimension by adding heat dissipation fins that increase the surface area for heat radiation. This dimensional extension allows the compact heat pipe to achieve effective heat dissipation by utilizing the vertical dimension for fin structure, maintaining high heat transfer efficiency while keeping the overall system compact and simple.
3Temperature
If active water cooling is used, then cooling function is provided, but additional power units are required
Solution Approach 1:
The heat pipe cooling system is entirely passive and self-powered, utilizing natural convection, phase change, and capillary action to circulate the working fluid. No external power source, pumps, or control systems are required, making the system energy-independent and ideal for space applications where power is at a premium and system reliability is critical.
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 heat pipe cooling structure ensures stable and reliable operation, extends thruster lifespan, and conserves resources by using a small amount of coolant, offering a compact, safe, and reliable solution suitable for cryogenic space environments.
Implementation Method 1
the cathode heat pipe includes an evaporation section and a condensation section
Implementation Method 2
the cathode heat pipe includes an evaporation section and a condensation section
Implementation Method 3
the cathode heat pipe includes an evaporation section and a condensation section
Implementation Method 4
The use of heat pipe plus radiation to complete the passive heat dissipation mode
Data Source
AI summary
The present disclosure provides a cooling structure of heat pipe for superconducting magneto plasma dynamic thruster having a cylindrical structure and includes a cathode, an intermediate connector and an anode. The cathode is arranged inside the intermediate connector, the anode is arranged outside the intermediate connector; the cathode is provided with a cathode cooling mechanism, and the anode is provided with an anode cooling mechanism. The cathode cooling mechanism includes a cathode heat pipe and a cathode heat dissipation fin. The anode heat pipe cooling mechanism includes an anode heat pipe and an anode heat dissipation fin.