Multi-layered Reactive Thin Film Solid Propellants
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Solution Overview
Problem
High-energy solid propellants face inefficiencies due to incomplete burning of metal fuels, physical obstructions, and energy losses from molten metal pooling and supercooling, leading to unstable burn rates and reduced specific impulse in rocket motors.
Innovation Solution
Incorporating multi-layered reactive thin films with chemically bonded metal and inorganic oxidizer layers into the propellant matrix, which self-oxidize and release energy quickly, reducing residence time and enhancing heat transfer, thereby stabilizing burn rates and increasing energy density.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If metal fuels are used in high-energy solid propellants, then energy density is improved, but burn completeness deteriorates due to incomplete burning and molten metal pooling
Solution Approach 1:
The metal fuel is segmented into thin film layers (e.g., aluminum layers of specific thickness ranges) rather than using bulk metal particles. This segmentation prevents molten metal pooling and ensures more complete combustion by increasing surface area to volume ratio, thereby resolving the contradiction between energy density and burn completeness.
Solution Approach 2:
The invention uses composite thin film structures combining metal layers with binder materials and oxidizer layers. This composite approach allows the metal fuel to maintain structural integrity while achieving complete combustion, simultaneously improving energy density utilization and burn reliability.
2Stability of the object's composition
If multi-layered reactive thin films are used, then burn rate stability is improved, but device complexity increases due to layered structure
Solution Approach 1:
The propellant is segmented into multiple thin functional layers (metal layers, oxidizer layers, binder layers) each with specific thicknesses and compositions. This segmentation enables precise control over burn rate characteristics while maintaining manufacturing feasibility through established thin film deposition techniques.
Solution Approach 2:
The invention controls burn rate stability by adjusting parameters such as layer thickness, material composition, and layer sequence in the thin film structure. By optimizing these parameters, the patent achieves stable burn rates without requiring overly complex manufacturing processes.
3Use of energy by moving object
If metal fuel particles are used, then specific impulse is reduced due to momentum losses, but energy content is high
Solution Approach 1:
The invention changes the physical form of metal fuel from particles to thin films, fundamentally altering combustion characteristics. This parameter change reduces momentum losses by preventing molten metal ejection while maintaining high energy content, thereby improving specific impulse.
Solution Approach 2:
The invention converts the potential harm of molten metal pooling and ejection into a benefit by using thin film structures that naturally prevent pooling. The same properties that would cause momentum losses in particle form (metal liquidity during combustion) are transformed into advantages through the thin film geometry, ensuring complete combustion without ejection losses.
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 use of reactive thin films in solid composite propellants improves burn consistency, reduces momentum losses, and increases specific impulse, leading to more efficient energy extraction and enhanced rocket motor performance.
Implementation Method 1
multi-layered reactive thin films with chemically bonded metal and inorganic oxidizer layers into the propellant matrix, which self-oxidize and release energy quickly
Implementation Method 2
reducing residence time and enhancing heat transfer, thereby stabilizing burn rates
Data Source
AI summary
Solid composite propellants are provided that include a matrix comprising an energetic oxidizer and a binder. A multi-layered reactive thin film is provided in the matrix. The reactive thin film includes metal and inorganic oxidizer. Methods of making the solid composite propellants are also provided.