Rectangular Combustion Chamber for Solid Propellant Thermal Erosion Testing
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Solution Overview
Problem
Current methods for characterizing thermal erosion behavior of thermal protection materials in solid propellant thrusters require costly and cumbersome 1/1 scale tests, limiting the evaluation and dimensioning of new materials, as reduced scale tests are not representative of full-scale conditions.
Innovation Solution
A thermal erosion test device using a plane plate with a rectangular combustion chamber and ultrasound/plasma capacitance sensors to simulate 1/1 scale conditions, allowing for accurate measurement of material degradation and stress zones, and a cylindrical shell to distribute pressure uniformly, enabling cost-effective testing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If reduced scale tests are performed using cylindrical extenders, then test cost and complexity are reduced, but the representativeness of thermal erosion behavior deteriorates
Solution Approach 1:
The invention creates a scaled-down model that copies the essential geometric and flow characteristics of full-scale thrusters. By maintaining similarity in combustion chamber shape, nozzle geometry, and flow patterns, the model reproduces representative thermal erosion behavior at reduced size, allowing reliable material evaluation without full-scale testing
Solution Approach 2:
The invention changes the scale parameters while maintaining dimensional relationships. By carefully selecting model dimensions that preserve key geometric ratios and flow characteristics, the system achieves representative testing at smaller scale. The model uses appropriate scaling factors for chamber size, nozzle throat diameter, and propellant grain geometry to replicate full-scale conditions
2Reliability
If 1/1 scale tests are performed, then the representativeness of thermal erosion behavior is maintained, but test cost and time consumption increase
Solution Approach 1:
The scaled model copies the critical geometric and flow features of full-scale thrusters, enabling representative thermal erosion testing in a smaller, faster system. The model preserves essential dimensional relationships while reducing overall size, allowing material evaluation without the time and cost of full-scale tests
Solution Approach 2:
The model performs partial testing by focusing on the most critical thermal erosion zones and material behaviors. Rather than replicating every aspect of full-scale operation, the model concentrates on measuring thermal erosion characteristics under representative conditions, achieving sufficient data for material selection and design optimization
3Measurement precision
If 1/1 scale tests are performed, then accurate erosion criterion determination is possible, but the ability to perform prior studies with new materials is lost
Solution Approach 1:
The scaled model serves multiple functions: it can test various thermal protection materials, evaluate different propellant formulations, and study various combustion chamber configurations. This universal testing capability allows prior studies with new materials using the same representative model, eliminating the need for separate full-scale tests for each material evaluation
Solution Approach 2:
The model creates a universal representative platform that copies essential full-scale characteristics while enabling flexible material testing. Once the model geometry and test protocol are validated, they can be used to evaluate any thermal protection material under representative conditions, providing accurate erosion criterion determination without requiring 1/1 scale tests for each material
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
Enables representative thermal erosion behavior testing at reduced scale, allowing for the development and dimensioning of thermal protection materials without the need for full-scale tests, while maintaining stress levels similar to 1/1 scale conditions.
Implementation Method 1
the device comprises means for holding a plate made of the thermal protection material for testing so that its faces a face of a block of solid propellant, the space between the plate and the face of the propellant block defining a combustion chamber
Implementation Method 2
expose a plate of thermal protection material to a tangential flow of combustion gas generated by a block of propellant
Implementation Method 3
the device includes means for measuring the variation in the degradation and the retreat of the surface of the plate of thermal protection material for testing
Implementation Method 4
a cylindrical shell to distribute pressure uniformly
Data Source
AI summary
The invention relates to a thermal erosion test device for testing thermal protection materials for use in a solid propellant thruster. The device comprises a support for holding a plate made of the thermal protection material for testing so that its faces a face of a block of solid propellant, the space between the plate and the face of the propellant block defining a combustion chamber of substantially rectangular shape, said chamber extending along said plate and opening out into a nozzle.