Auxiliary Gas-Generator Pressurization to Reduce Spacecraft Mass
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Solution Overview
Problem
Existing spacecraft tank pressurization systems using inert gases incur additional mass and pressure-related risks, while conventional autogenous systems require additional fuel management systems and complex tank designs.
Innovation Solution
A pressurization system utilizing an auxiliary unit with an auxiliary oxidizer tank, gas generator, and turbine to autonomously generate pressurizing gas for fuel and oxidizer tanks, eliminating the need for additional fuel and simplifying tank design by integrating attitude control and propulsion functions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If inert gas systems are used for tank pressurization, then reliable pressurization is achieved, but additional mass and pressure-related risks increase
Solution Approach 1:
The system uses the spacecraft's own fuel and oxidizer to generate pressurization gas through controlled combustion in the gas generator, eliminating the need for separate inert gas tanks and reducing overall system mass while maintaining reliable pressurization
2Weight of moving object
If autogenous pressurization systems are used, then mass is reduced, but device complexity increases due to additional fuel management systems
Solution Approach 1:
The pressurization function is merged with the existing propulsion system by using the gas generator and turbine that are already part of the engine cycle, eliminating the need for separate fuel management systems and reducing overall device complexity
Solution Approach 2:
The gas generator serves dual purposes: it generates power for the turbine/compressors and simultaneously produces pressurization gas for the fuel and oxidizer tanks, making the system multi-functional and reducing complexity
3Reliability
If high pressure is used in inert gas systems, then reliable pressurization is achieved, but pressure-related risks increase
Solution Approach 1:
The system generates pressurization gas at controlled, lower pressures through the gas generator compared to conventional high-pressure inert gas systems, reducing pressure-related risks while maintaining reliable tank pressurization through the compressor
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
Enables efficient, autonomous tank pressurization with reduced mass and complexity, allowing for simplified tank design and integrated attitude control during spacecraft operations.
Implementation Method 1
The gas generator can preferably serve to catalytically or thermolytically decompose the oxidizer from the auxiliary tank (without adding fuel) and thus generate high-energy exhaust gas for the turbine.
Implementation Method 2
The gas generator can preferably serve to catalytically or thermolytically decompose the oxidizer from the auxiliary tank (without adding fuel) and thus generate high-energy exhaust gas for the turbine.
Implementation Method 3
a turbine connected to the auxiliary tank. The auxiliary tank is specifically intended to contain oxidizer (for example, preferably highly concentrated hydrogen peroxide) and is therefore referred to below as the 'auxiliary oxidizer tank.'
Implementation Method 4
A portion of oxidizer is introduced into the fuel tank, inducing a hypergolic chemical reaction that leads to gas generation and heat input into the tank's headspace, thus maintaining stable tank pressure during fuel tank emptying.
Data Source
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AI summary
Disclosed is a pressurization system 100, 200, 300, 400 for a spacecraft having a fuel tank 60, an oxidizer tank 50, and an auxiliary unit. The auxiliary unit comprises an auxiliary oxidizer tank 10, an auxiliary gas generator 25 fed from the auxiliary oxidizer tank, and an auxiliary turbine 26 connected thereto. The auxiliary unit is configured to pressurize at least the fuel tank 60 hypergolically, chemically, and/or by evaporating fuel by means of a heat exchanger. Also disclosed are a spacecraft having such a pressurization system and a main combustion chamber 1, and a method for operating such a spacecraft.