Modular Electric Propulsion Engine Design for Rapid Reconfiguration
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Solution Overview
Problem
Current electric propulsion (EP) rocket engines are highly specialized, complex, and costly to develop and maintain, with custom designs leading to rapid obsolescence and limited reconfigurability, making them unsuitable for rapid mission changes and efficient production.
Innovation Solution
A modular design approach using standard interfaces for major components such as discharge chambers, cathode assemblies, and ion optics, allowing for interchangeable sub-assemblies to create various EP rocket engines from a small set of interchangeable parts, facilitating accelerated development and user-specified configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If custom designs are used for each EP rocket engine to meet specific mission requirements, then the engine can be optimized for the specific mission, but the development time and cost increase significantly
Solution Approach 1:
The EP rocket engine is divided into modular sub-assemblies (discharge chamber, ion optics assembly, cathode assemblies, magnetic coil assemblies, power processing units) that can be independently designed, tested, and manufactured. This segmentation allows parallel development of multiple modules, reducing overall development time while maintaining mission-specific optimization capabilities through selective combination of modules.
Solution Approach 2:
Standardized interfaces and common sub-assemblies are designed to be reusable across multiple engine variants and mission types. The modular architecture with standardized connection protocols enables the same basic modules to be configured for different missions, reducing development time for new missions while maintaining adaptability through reconfiguration rather than complete redesign.
2Adaptability or versatility
If custom designs are used for each EP rocket engine, then the engine can be optimized for the specific mission, but the cost increases significantly
Solution Approach 1:
By segmenting the engine into standardized modules, manufacturing can be optimized for each module independently using specialized production techniques. Common modules can be manufactured in larger quantities at lower unit costs, while mission-specific variations only require different combinations of these pre-manufactured modules, reducing overall manufacturing cost.
Solution Approach 2:
Standardized sub-assemblies with universal interfaces can be manufactured once and reused across multiple engine variants, eliminating redundant manufacturing costs. The modular design allows a single production line to support multiple mission configurations by simply reconfiguring the assembly of standardized components, significantly reducing per-unit manufacturing cost.
3Adaptability or versatility
If traditional EP thrusters are designed as one-and-done items, then they can meet specific mission requirements, but they cannot be readily reconfigured or repaired
Solution Approach 1:
The engine is divided into discrete, independently replaceable sub-assemblies connected by standardized interfaces. This segmentation enables individual modules to be removed, replaced, or repaired without affecting the entire system, significantly improving ease of repair and reconfigurability while maintaining mission-specific performance through selective module replacement.
Solution Approach 2:
The modular design with standardized interfaces creates a dynamic system where sub-assemblies can be reconfigured for different missions or operational requirements. This dynamic reconfigurability allows the same hardware platform to adapt to changing mission needs, extending the operational lifecycle and reducing the need for complete system replacement.
4Adaptability or versatility
If custom EP rocket engines are designed for each mission, then they can be optimized for specific requirements, but they become obsolete rapidly and cannot accommodate changes
Solution Approach 1:
The modular design with standardized interfaces creates a universal platform that can serve multiple missions and operational requirements. By reconfiguring combinations of standardized modules rather than designing entirely new systems, the service life of the engine platform is extended significantly, reducing obsolescence while maintaining mission-specific optimization capabilities.
Solution Approach 2:
The system is designed to be dynamically reconfigurable, allowing adaptation to new mission requirements through module reconfiguration rather than complete replacement. This dynamic capability extends the operational lifespan of the engine platform by enabling it to evolve with changing mission needs, thereby increasing the duration of useful service.
Data Source
AI summary
A method includes producing an electric propulsion (EP) rocket engine. The method selects a core discharge chamber. A discharge cathode assembly (DCA) is selected along with a DCA common interface (CI). The DCA CI is connected to the core discharge chamber and the DCA is connected to the DCA CI. A neutralizer cathode assembly (NCA) is selected with an NCA CI. The NCA CI is connected to the core discharge chamber and the NCA is connected to the NCA CI. An ion optics assembly (IOA) is selected along with an IOA CI. The IOA CI is connected to the core discharge chamber and the IOA is connected to the IOA CI. The three common interfaces: DCA CI, NCA CI, and IOA CI allow for different subassemblies to be connected to their respective common interfaces—for purposes of re-configurability to accommodate changes in operational requirements, or replacement of subassemblies.