Universal EPDM Rocket Motor Insulation via Composite Formulation
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Solution Overview
Problem
Conventional rocket motor insulations require multiple materials for different sections, increasing manufacturing complexity and cost due to the need for varying mechanical, thermal, and ablative properties, while also being prone to erosion and penetration issues from high-energy particles and fuels.
Innovation Solution
A universal precursor composition comprising ethylene propylene diene monomer (EPDM), zinc oxide, silica, polymerized 1,2-dihydro-2,2,4-trimethylquinoline, solid chlorinated paraffin, stearic acid, a five carbon petroleum hydrocarbon, trimethylolpropane trimethacrylate, and a peroxide, which can be cured to form a single insulation that provides improved mechanical, thermal, and ablative properties across different regions of the rocket motor, reducing the need for multiple insulations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If different insulations are used on different sections of the case to provide desired mechanical, thermal, and ablative properties, then the performance requirements are met, but the manufacturing complexity and cost increase
Solution Approach 1:
The patent applies universality by developing a single insulation composition that can be used across all sections of the rocket motor case. This composition is formulated to provide the necessary mechanical, thermal, and ablative properties universally, eliminating the need for multiple specialized insulation materials for different sections.
Solution Approach 2:
The patent employs composite materials by creating an insulation composition containing silica filler (20-60 parts by weight per 100 parts rubber) combined with EPDM rubber and various additives. This composite structure provides enhanced mechanical strength, thermal resistance, and ablative properties in a single material system that can replace multiple conventional insulation types.
2Reliability
If conventional silica-filled EPDM insulations are used, then good insulative properties are achieved, but the insulation is prone to erosion and penetration from high-energy particles and fuels
Solution Approach 1:
The patent uses composite materials by formulating an insulation composition with silica filler (20-60 parts by weight per 100 parts rubber) combined with EPDM rubber, zinc oxide, stearic acid, and other additives. This composite structure enhances resistance to erosion and penetration from high-energy particles while maintaining insulative properties.
Solution Approach 2:
The patent applies parameter changes by modifying the chemical composition and physical properties of the insulation material. Specifically, it adjusts the silica content (20-60 parts per 100 parts rubber), incorporates cross-linking agents, and adds protective compounds to change the material's resistance parameters against particle erosion and fuel penetration.
3Device complexity
If a single insulation type is used across all sections, then manufacturing complexity and cost are reduced, but it may not provide optimal performance for all sections
Solution Approach 1:
The patent achieves universality by formulating a single insulation composition that can serve all sections of the rocket motor case. This composition is designed with balanced properties to meet the performance requirements of different sections without requiring material differentiation, thus simplifying manufacturing while maintaining reliability.
Solution Approach 2:
The patent uses parameter changes by optimizing the composition ratios of its components (silica: 20-60 parts, EPDM rubber: 100 parts, zinc oxide: 1-5 parts, stearic acid: 1-3 parts, etc.) to create a material with balanced mechanical, thermal, and ablative properties that can perform adequately across all motor sections.
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
The universal insulation offers comparable or improved mechanical, physical, and ablative properties to conventional silica-filled EPDM insulations, reducing manufacturing complexity and cost by using a single insulation type, while providing effective protection against heat, erosion, and extreme conditions without the need for fibers, thus enhancing the reliability and efficiency of rocket motors.
Implementation Method 1
The uncured composition includes a peroxide, and the cured insulation is a reaction product of EPDM, zinc oxide, silica, polymerized 1,2-dihydro-2,2,4-trimethylquinoline, a solid chlorinated paraffin, stearic acid, a five carbon petroleum hydrocarbon, trimethylolpropane trimethacrylate, and the peroxide
Data Source
AI summary
A precursor composition comprising, before curing, ethylene propylene diene monomer (EPDM), zinc oxide, silica, polymerized 1,2-dihydro-2,2,4-trimethylquinoline, a solid chlorinated paraffin, stearic acid, a five carbon petroleum hydrocarbon, trimethylolpropane trimethacrylate, and a peroxide. A rocket motor including a reaction product of the precursor composition and a method of insulating a rocket motor.