Fault-Tolerant Spacecraft Propulsion Using Segmented Bipropellant Thrusters
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Solution Overview
Problem
Current spacecraft propulsion systems are not fault-tolerant, scalable, or fuel-efficient, particularly for high thrust requirements in orbit transfer and maneuvering, and they incur increased production costs and time due to reliance on less efficient engines and complex propellant line configurations.
Innovation Solution
The implementation of multiple high efficiency bipropellant Delta V thrusters integrated within a cylindrical core member, providing scalable high thrust capabilities and redundancy by allowing operation of a subset of engines in case of failure, reduces reliance on monopropellant engines and simplifies propellant line management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple high thrust bipropellant engines are used, then fault tolerance and scalability are improved, but device complexity increases
Solution Approach 1:
The propulsion system is divided into multiple independent high thrust bipropellant engines (DV thrusters) that can operate individually or in combination. Each engine is a self-contained unit with its own propellant storage and delivery system, allowing the system to segment the total thrust requirement into manageable components that can fail independently without compromising the entire system.
Solution Approach 2:
The multiple DV thrusters are designed with universal compatibility, where each engine can perform the same function (high thrust propulsion) and can be used for multiple mission phases including orbit transfer, relocations, and attitude control. The engines are integrated into the spacecraft structure with standardized mounting and propellant delivery interfaces, enabling flexible configuration for different operational requirements.
2Power
If multiple high thrust bipropellant engines are used, then scalability and thrust capability are improved, but manufacturing cost and production time increase
Solution Approach 1:
The propulsion system uses multiple standardized high thrust bipropellant engine modules that can be manufactured independently and assembled into the final configuration. Each module is designed with standardized interfaces and propellant delivery systems, allowing for parallel production and reducing overall manufacturing complexity compared to building a single large engine system.
Solution Approach 2:
The system allows for flexible configuration by varying the number and arrangement of active DV thrusters based on specific mission requirements. This scalability enables the same basic engine design to serve multiple thrust levels and application scenarios, reducing the need for specialized custom-engine manufacturing for different mission phases.
3Device complexity
If monopropellant engines are used, then device complexity is reduced, but fuel efficiency deteriorates
Solution Approach 1:
The system transitions from monopropellant to bipropellant engines, changing the fundamental operating parameter of the propulsion system. The bipropellant DV thrusters use a combination of fuel and oxidizer (such as hydrazine and dinitrogen tetroxide) to achieve higher specific impulse and improved fuel efficiency compared to monopropellant systems, while the added complexity of the bipropellant delivery system is offset by the performance benefits.
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 approach enables fault-tolerant and scalable high thrust propulsion with reduced production costs and time, achieving efficient fuel use and adaptable thrust levels for various spacecraft operations while maintaining thermal control and minimizing physical interferences.
Implementation Method 1
multiple high efficiency engines to provide fault-tolerant and scalable high thrust
Implementation Method 2
high thrust bipropellant engines
Implementation Method 3
Delta V thrusters mounted within a cylindrical core member... providing scalable high thrust capabilities
Data Source
AI summary
Systems and methods of the present disclosure can be utilized to provide an improved propulsion system that uses multiple high efficiency engines to provide fault-tolerant and scalable high thrust for orbit transfer and maneuvering over life. An exemplary spacecraft includes a base panel, a cylindrical core member mounted to the base panel, multiple DV thrusters mounted within the cylindrical core member, and multiple reaction engine assemblies mounted to the base panel outside the cylindrical core member. Each of the DV thrusters has a thrust level that is greater than a thrust level of each of the reaction engine assemblies. The multiple DV thrusters are operated for velocity control, with attitude control being performed by off-pulsing at least one of the multiple DV thrusters.