Rocket Propellant Bypass Pump Upstream Valve Segmentation
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Solution Overview
Problem
Existing rocket engine propellant supply devices face challenges in efficiently utilizing propellant for purposes other than main combustion, affecting performance and stability, particularly due to limitations in bypassing propellant flow without compromising engine performance.
Innovation Solution
Incorporation of a bypass pump connected upstream of the valve in the propellant supply line, allowing propellant to be diverted to auxiliary pipes regardless of valve state, with a design that maintains optimal temperature and reduces mechanical complexity, using an electric pump with hermetically insulated stator and cooling mechanisms to ensure reliability and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If propellant is taken off for auxiliary purposes through the main supply line downstream of the valve, then auxiliary functions can be supplied, but the valve state (open/closed) restricts the ability to take off propellant and operating stability is compromised
Solution Approach 1:
The propellant supply system is segmented into a main supply line (through the valve and main pump) and a separate bypass line (with bypass pump connected upstream of the valve). This segmentation allows the bypass pump to independently extract propellant for auxiliary functions regardless of the valve state, while the main supply line continues to serve the combustion chamber, thereby maintaining operating stability and enabling auxiliary versatility simultaneously.
2Adaptability or versatility
If a bypass pump is connected downstream of the valve, then auxiliary propellant supply is possible, but the pump operates at low flow rates causing instability and requires warm-up time
Solution Approach 1:
The bypass pump is positioned upstream of the valve in the propellant supply line, allowing it to draw propellant directly from the tank before the main flow is restricted by the valve. This preliminary positioning ensures the bypass pump operates at high flow rates from the start, eliminating the need for warm-up time and preventing operating instability associated with low flow rates.
3Ease of operation
If the bypass pump is positioned far from the propellant tank, then installation flexibility is improved, but the pump is not at propellant temperature requiring warm-up time
Solution Approach 1:
The bypass pump is merged with the main supply line structure, mounted on the supply line itself rather than being separately positioned far from the tank. This integration ensures the pump inlet is always close to the propellant source, maintaining propellant temperature at the pump inlet and eliminating warm-up time, while the overall system design preserves installation flexibility.
4Device complexity
If auxiliary propellant supply is taken from downstream of the valve, then the valve controls main supply, but the auxiliary supply is restricted by valve position and structure becomes complex
Solution Approach 1:
The system is divided into independent bypass and main supply paths. The bypass pump with its dedicated bypass line creates an independent auxiliary supply path that draws propellant upstream of the valve, making auxiliary supply independent of valve position. This segmentation actually simplifies the overall structure by providing clear functional separation between main and auxiliary supply controls.
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 solution enables efficient propellant utilization for auxiliary functions, minimizing start-up time and operating instability, while maintaining the propellant's temperature and reducing the risk of mechanical stress, thus enhancing the rocket engine's performance and reliability.
Implementation Method 1
at least one bypass pump connected in bypass to the tank upstream of the valve, to supply an auxiliary pipe serving an auxiliary function of the rocket engine
Implementation Method 2
the rotor being disposed in a rotor chamber whose stator is hermetically insulated
Implementation Method 3
using an electric pump with hermetically insulated stator and cooling mechanisms to ensure reliability and efficiency
Data Source
Figure 1A
Figure 1B
Figure 2
AI summary
A device for supplying rocket engine propellant (10A, 10B) comprising at least one propellant tank (10, 11), a combustion chamber (18), a supply pipe (12, 13) extending from the tank (10, 11) to the combustion chamber (18) to supply propellant to the combustion chamber. A valve (14, 15) and a main pump (16, 17) are disposed respectively on the supply pipe. The rocket engine device further comprises at least one bypass pump (20, 21, 120, 220) connected in bypass to the tank upstream of the valve, in order to supply an auxiliary pipe (22, 23, 122, 222) carrying out an auxiliary function of the rocket engine.