Propellant Vaporization Using Thermal Storage Spheres
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Solution Overview
Problem
Current cryogenic engine ignition systems face challenges in efficiently vaporizing propellants due to thermal inertia in supply circuits, leading to incomplete vaporization and performance issues, with existing solutions either being mass-inefficient or complex in design.
Innovation Solution
A system using storage spheres made of polyamides and polytetrafluoroethylene, compacted between thrust plates with holes, stores calorific energy by injecting hot gas like helium, facilitating efficient heat transfer and vaporization of propellants within the reservoir.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If propellant is vaporized using conventional heat exchange methods, then the propellant can be supplied to the igniter, but thermal inertia prevents complete vaporization and performance deteriorates
Solution Approach 1:
The invention changes the thermal parameters of the system by pre-heating the propellant using hot gas (helium) before it reaches the vaporization zone. This pre-heating reduces the thermal inertia effect and ensures complete vaporization. The hot gas temperature and flow rate are controlled to optimize the heating process.
Solution Approach 2:
The propellant is pre-heated in advance using hot gas before entering the main vaporization zone. This preliminary heating action reduces the amount of heat required in the subsequent vaporization stage, ensuring complete vaporization and improving ignition performance.
2Reliability
If passive systems use cylinders for high-pressure propellant storage, then propellant can be stored and controlled, but mass increases
Solution Approach 1:
The invention extracts the heavy high-pressure cylinders from the system and replaces them with a lightweight alternative: a reservoir containing porous material saturated with liquid propellant. The propellant is delivered through capillary action and evaporation, eliminating the need for heavy pressure vessels while maintaining reliable storage and control.
Solution Approach 2:
The mechanical high-pressure storage system is replaced with a thermal-based system using evaporation and capillary action. The heavy cylinders and pressure control mechanisms are substituted with a lighter reservoir system that uses heat transfer and surface tension for propellant delivery.
3Reliability
If passive systems use convective heat exchange for vaporization, then propellant can be vaporized, but design complexity increases due to low heat transfer coefficients
Solution Approach 1:
The invention uses porous material (wool or foam) saturated with liquid propellant as the heat exchange medium. The porous structure provides extremely large surface area for heat transfer, enabling efficient vaporization without complex heat exchanger designs. The capillary action within the porous material also aids in propellant distribution.
Solution Approach 2:
The invention transitions from conventional 2D heat exchange surfaces to a 3D porous structure with immense surface area. This dimensional change provides vastly increased heat transfer area within a compact volume, simplifying the overall system design while maintaining efficient vaporization.
4Reliability
If active systems use heat exchangers and combustion chambers for propellant heating, then propellant can be vaporized, but mass increases
Solution Approach 1:
The invention extracts and removes the heavy heat exchangers and combustion chambers from the system. Instead, it uses a simple reservoir with porous material that utilizes evaporation and capillary action for propellant vaporization, dramatically reducing system mass while maintaining reliable vaporization.
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 ensures complete vaporization of propellants with reduced mass and complexity, providing a flexible and efficient propellant supply system for cryogenic engines, suitable for space applications.
Implementation Method 1
stores calorific energy in a set of storage spheres by injecting a hot gas into said reservoir
Implementation Method 2
injecting a hot gas into the reservoir, said hot gas being taken from a gaseous reservoir
Implementation Method 3
the propellant to be vaporized passes through said reservoir so as to be vaporized by heat exchange with said storage spheres
Implementation Method 4
vaporized by heat exchange with said storage spheres
Implementation Method 5
one of the upstream and downstream plates being subjected to a thrusting force towards the other of the upstream and downstream plates so as to compact the storage spheres contained in the internal volume
Data Source
Figure 1~2
AI summary
System (100) for supplying an igniter with propellant, comprising - a reservoir (10) having an intake (11) and a discharge (12), - a liquid propellant supply line connected to the intake (11) of the reservoir (10), - a propellant discharge line connecting a discharge (12) of the reservoir (10) to an igniter (40), characterized in that said reservoir (10) has an internal volume filled with heat storage spheres (20), said storage spheres (20) being designed to store heat and to transmit it to a fluid passing through said reservoir (10) so as to evaporate a liquid propellant passing through said reservoir (10).