Off-Center Capacitive Pogo Corrector for Rocket Propellant Feed
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Solution Overview
Problem
Existing capacitive pogo effect corrector systems for liquid propellant rockets are bulky, non-modular, and difficult to assemble, especially in confined spaces, due to their centralized tank design and welding requirements, which limits their effectiveness and flexibility.
Innovation Solution
A capacitive pogo effect corrector system with a tank design that offsets its inner volume relative to the feed pipe, allowing for reduced size and modular assembly, featuring a bent feed pipe part surrounded by the tank's inner volume, eliminating the need for a rectilinear segment and enabling assembly without welding, and incorporating compartment walls to prevent malfunction under lateral acceleration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If the tank is centered around the feed pipe part, then the communication orifices are uniformly distributed, but a rectilinear segment must be provided upstream from the tank to allow flange assembly, which increases the overall size
Solution Approach 1:
The patent applies asymmetry by positioning the tank off-center relative to the feed pipe part. The tank is arranged such that its central axis is offset from the feed pipe's central axis, allowing the flange to be positioned at a location that does not require additional rectilinear segments, thus reducing the overall size while maintaining assembly ease
Solution Approach 2:
The patent utilizes dimensional repositioning by moving the tank along the radial dimension relative to the feed pipe. This allows the flange assembly area to be relocated to a position that eliminates the need for extra linear space, effectively solving the space constraint problem through spatial rearrangement
2Adaptability or versatility
If the tank is centered around the feed pipe part, then the structure is symmetric and simple, but the system cannot be used in small spaces or on bends with small radius of curvature
Solution Approach 1:
The off-center arrangement of the tank provides adaptability to confined spaces and bends with small radius of curvature. By positioning the tank asymmetrically, the system can be installed in locations where symmetric arrangements would not fit, such as tight corners or curved sections of piping
Solution Approach 2:
The patent introduces dynamic adaptability by allowing the system configuration to adjust to different spatial constraints. The off-center tank design enables the system to adapt to various installation environments including small spaces and curved paths, making the system more versatile without requiring complex mechanical adjustment mechanisms
3Reliability
If the tank is entirely welded to the feed pipe, then the connection is strong and permanent, but the system is neither modular nor capable of being disassembled, making it difficult to change the configuration of communication orifices
Solution Approach 1:
The patent applies segmentation by introducing a flange connection that divides the system into separable components. The flange acts as a modular interface between the tank and feed pipe, allowing the system to be disassembled and reconfigured while maintaining connection strength during operation
Solution Approach 2:
The flange connection transforms the static, permanent welded joint into a dynamic, reconfigurable connection. This allows the system to transition between assembled and disassembled states, enabling modularity and ease of reconfiguration while maintaining structural integrity during operation
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 system achieves a compact, modular, and efficient pogo effect correction, allowing for wider operational ranges and easier adaptation to various rocket configurations while maintaining satisfactory hydraulic behavior and reducing the risk of malfunction during flight.
Implementation Method 1
a constant flow of gas (e.g. helium (He)) is injected into the upper part of the tank so as to maintain a bubble of gas in the tank
Implementation Method 2
a tank of a hydraulic accumulator is arranged around the pipe of a line for feeding the rocket engine with liquid propellant
Implementation Method 3
a dip tube connects the liquid-gas interface to the liquid propellant feed pipe
Implementation Method 4
The flow direction E of the liquid propellant is shown by an arrow in FIG. 1
Data Source
AI summary
A pogo effect corrector system for a feed system for feeding a rocket engine with liquid propellant, the corrector system comprising: a feed pipe part for feeding liquid propellant that is configured to be connected both upstream and downstream to a liquid propellant feed pipe of the feed system; and a hydraulic accumulator comprising a tank connected to the feed pipe part via at least one communication orifice; the corrector system being characterized in that: at least a portion of the feed pipe part is at least partly surrounded by the inner volume of the tank; with each cross-section of said portion relative to its central axis being at least partly surrounded by the corresponding cross-section of the inner volume of the tank, in such a manner that the corresponding cross-section of the inner volume of the tank is off-center relative to said cross-section of said portion.