High Triple Point Propellant Phase Control via Combustion Pressure
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Solution Overview
Problem
High triple point propellants pose challenges during rocket engine ignition due to phase changes from liquid to gas and solid, causing plugging and uneven flow issues, and existing mechanical methods are inadequate for maintaining pressure and enabling engine relight.
Innovation Solution
Delivering a flow of combustible gas downstream from a high triple point propellant valve, combusting it to achieve a predetermined pressure that maintains the propellant in a stable phase, and terminating the gas flow simultaneously with propellant delivery to ensure consistent pressure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If mechanical plugs or burst discs are used to maintain pressure in the combustion chamber, then the propellant can be kept above its triple point pressure, but the devices are single-use, cannot enable engine relight, and cause dramatic flow rate increases that may drop pressure below the triple point
Solution Approach 1:
The patent replaces mechanical pressure control devices (plugs, burst discs) with a combustion-based pressure control system. A combustion source is ignited to generate combustion products that pressurize the combustion chamber, maintaining pressure above the triple point. This substitution enables continuous operation and relight capability, as the combustion source can be reignited, unlike single-use mechanical devices.
Solution Approach 2:
The patent changes the method of pressure control from mechanical to thermal-chemical. By controlling the combustion of a separate fuel source, the system dynamically maintains chamber pressure within the required range. This allows for adjustable and continuous pressure control, enabling both initial ignition and subsequent relight operations.
2Stability of the object's composition
If the combustion chamber pressure is kept above the triple point pressure, then the propellant remains in liquid phase for steady flow, but mechanical devices used to build pressure must be released to allow propellant flow, causing pressure to drop and potentially forming solid phases
Solution Approach 1:
The patent introduces combustion products as an intermediary medium to transfer pressure to the propellant. The combustion source generates high-pressure combustion products that act as a mediator, transmitting pressure to the liquid propellant without direct mechanical contact. This allows the propellant to be delivered at controlled rates while maintaining pressure above the triple point, preventing solid phase formation.
Solution Approach 2:
The combustion source continues to burn during propellant delivery, maintaining continuous pressure above the triple point. This continuous action ensures the propellant remains in liquid phase throughout the delivery process, enabling steady flow without intermittent solid phase formation that would occur with batch mechanical pressure devices.
3Reliability
If mechanical plugs are set at predetermined pressure settings influenced by ambient temperature, then pressure control is achieved, but the set pressure varies with temperature changes and cannot adapt to different operating conditions
Solution Approach 1:
The patent transitions from static mechanical pressure settings to dynamic combustion-based pressure control. The combustion source can be adjusted in real-time to maintain pressure despite temperature variations. This dynamic control allows the system to adapt to changing ambient conditions and different operating requirements, providing both reliability and versatility.
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 method maintains the high triple point propellant in a predetermined phase throughout the flow from the tank to the combustion chamber, preventing phase changes and enabling reliable engine startup and relight.
Implementation Method 1
combusting the combustible gas to achieve a predetermined pressure in the rocket engine
Implementation Method 2
the state of the liquid propellant will begin to change from liquid to a gas and solid
Data Source
AI summary
Methods, systems and apparatuses are disclosed for delivering high triple point propellant to a rocket engine and maintaining the desired phase of the propellant during engine ignition.