Cryogenic Rocket Pressurization Using Fuel Cell Gas Accumulators
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Solution Overview
Problem
Conventional rocket propulsion systems face inefficiencies in energy use and mass reduction, limiting payload capacity due to reliance on heavy components like turbo pumps, compressors, and inert gas vessels for pressurization, and lack of efficient energy conversion and propellant utilization.
Innovation Solution
The system employs gas pressure accumulators charged during the ballistic phase using an energy conversion unit with a fuel cell and high-pressure electrolysis cell, enabling electrical energy generation and propellant reuse, eliminating the need for conventional power sources and heavy pressurization vessels, and allowing for efficient propellant distribution and thrust generation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional turbo pumps, compressors, and inert gas vessels are used for pressurization and power generation, then reliable propellant delivery is achieved, but system mass increases and energy efficiency decreases
Solution Approach 1:
The patent extracts and eliminates heavy conventional components (turbo pumps, compressors, inert gas vessels) by replacing them with a gas pressure accumulator system charged during ballistic phase, thereby reducing system mass while maintaining propellant delivery reliability through the accumulated pressure
Solution Approach 2:
The gas pressure accumulators are charged with propellant under pressure during the ballistic phase before the propulsion phase begins, preparing the system in advance to eliminate the need for heavy pumps and compressors during actual propulsion operations
2Power
If conventional APU with internal combustion engine is used for power generation, then electrical energy is generated, but system mass increases and energy efficiency decreases
Solution Approach 1:
The patent replaces the mechanical internal combustion engine-based APU with an electrochemical fuel cell system that generates electrical energy through electrochemical reactions, eliminating heavy mechanical components while improving energy efficiency
Solution Approach 2:
The fuel cell system serves multiple functions: generating electrical energy for system operations, producing water as a byproduct that can be utilized, and operating efficiently without the mass penalty of conventional power generation systems
3Stability of the object's composition
If gaseous propellant is released unused into space, then tank pressure is maintained, but propellant utilization efficiency decreases
Solution Approach 1:
Instead of discarding gaseous propellant into space, the patent recovers it by directing it to the fuel cell system where it is utilized for electrical energy generation, thereby converting what would be waste into a useful resource
Solution Approach 2:
The patent converts the potentially harmful waste discharge of gaseous propellant into a beneficial resource by using it as fuel for the fuel cell, transforming a loss into a gain for electrical energy production
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 configuration significantly increases energy efficiency, reduces mass, and enhances payload capacity by utilizing non-propellant masses for energy generation and optimizing propellant use, eliminating the need for heavy components and conventional power sources.
Implementation Method 1
an energy conversion unit, which is designed at least to charge the first and the second gas pressure accumulators
Implementation Method 2
at least one high-pressure electrolysis cell, which is preferably operated with the electrical energy provided by the fuel cell, in order to split the supplied reaction product back into the first propellant and into the second propellant
Implementation Method 3
a first supply circuit of the first gas tank is connected to the first cryogenic tank and comprises a heat exchanger so as to vaporize, with heat released from the at least one auxiliary propulsion unit, a flow of liquid of the first propellant
Data Source
AI summary
A rocket propulsion system comprising a first cryogenic tank and a second cryogenic tank, wherein the first cryogenic tank is filled with a first propellant, and the second cryogenic tank is filled with a second propellant, for purposes of feeding at least one repeatedly ignitable main propulsion unit in a propulsion phase of the rocket propulsion system. For purposes of tank pressurization via at least a low level of acceleration in a ballistic phase, a first auxiliary propulsion unit can be operated by means of a first gas pressure accumulator, and at least one further auxiliary propulsion unit can be operated by means of a further gas pressure accumulator, and the rocket propulsion system is assigned an energy conversion unit, which is designed at least to charge the first and the second gas pressure accumulator, preferably in the ballistic phase.