3D-Printed Rocket Engine Fuel Grains for Continuous Thrust Control
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Solution Overview
Problem
Existing 3D printing methods for rocket fuel grains face inefficiencies, such as excessive waste, labor, energy consumption, thermal heterogeneity, and material incompatibilities, leading to stress fractures and limited performance enhancements, while conventional methods struggle to produce complex geometries and tailored fuel formulations for optimized rocket propulsion.
Innovation Solution
A 3D-printable rocket engine design utilizing additive manufacturing to create multi-grained fuel grains with embedded sensors, allowing continuous monitoring and modification of fuel/oxidizer ratios, solids content, and mechanical properties, enabling controlled ballistics and thrust profiles through a system of interconnected chambers and nozzles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Shape
If conventional 3D printing methods are used to manufacture fuel grains, then complex geometries can be achieved, but material waste, labor, and energy consumption increase significantly
Solution Approach 1:
The patent combines multiple manufacturing operations (mixing, shaping, and curing of propellant material) into a single additive manufacturing process. The system integrates material deposition and forming in one continuous process, eliminating the need for separate mixing and molding operations that would generate waste and require additional labor.
Solution Approach 2:
The patent utilizes controlled parameter changes during the additive manufacturing process, specifically varying the composition and properties of propellant material as it is deposited layer by layer. This allows optimization of material usage and reduction of waste while maintaining the desired complex geometry.
2Shape
If conventional 3D printing methods are used to manufacture fuel grains, then complex geometries can be achieved, but production time increases due to excessive labor
Solution Approach 1:
The patent employs accelerated curing mechanisms that enable rapid solidification and setting of the propellant material during deposition. This accelerated process significantly reduces the time required for each layer to set, thereby reducing total production time while maintaining complex geometries.
Solution Approach 2:
The additive manufacturing system operates continuously, depositing and curing propellant material in an uninterrupted sequence. This continuous process eliminates idle time between operations and maintains steady production flow, reducing overall production time compared to batch processing methods.
3Shape
If conventional 3D printing methods are used to manufacture fuel grains, then complex geometries can be achieved, but thermal heterogeneity causes stress fractures
Solution Approach 1:
The patent implements localized control of thermal parameters during the additive manufacturing process. Different regions of the fuel grain receive tailored thermal treatment based on their specific geometric characteristics and material composition, ensuring uniform thermal stress distribution and preventing stress fractures in complex geometries.
Solution Approach 2:
The system incorporates preliminary thermal management measures during the deposition process, controlling the temperature gradient and cooling rate before stress can develop. This preventive approach cushions against thermal heterogeneity and avoids the formation of stress fractures in the complex geometry.
4Ease of manufacture
If conventional 3D printing methods are used to manufacture fuel grains, then production can be performed, but fuel formulation customization is limited
Solution Approach 1:
The additive manufacturing system employs dynamic control of material composition during the printing process. The system can adjust fuel formulation parameters in real-time based on the specific requirements of different regions of the fuel grain, enabling extensive customization while maintaining ease of manufacture through automated control.
Data Source
AI summary
A rocket motor comprising a non-permeable outer shell, an intra-wall channel between the non-permeable outer shell and an annular section, and a center chamber formed at least in part by a first propellant is disclosed. The first propellant is made up of a multi-grained fuel grain, and the center chamber is further formed by an annular section. The intra-wall channel is configured to permit combustion gases to flux between the non-permeable outer shell and the annular section. The annular section configured to permit combustion gases to flux through pores embedded within the annular section.