Staggered Joint Thermal Protection Panels for Reentry Erosion
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Solution Overview
Problem
Traditional thermal protection systems for space reentry vehicles rely on single-piece heat shields that can lead to overheating and erosion due to airflow alignment along long straight seams, which are not effectively managed by existing technologies.
Innovation Solution
The use of heat-resistant panels with staggered joints, where the joint edges are deliberately shaped to be non-straight and non-uniform, reducing airflow alignment and erosion by creating gaps that are filled with a heat-resistant filler material, thereby minimizing overheating and premature joint erosion during reentry.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If traditional single-piece heat shields are used, then manufacturing is simpler, but airflow alignment along long straight seams causes overheating and erosion
Solution Approach 1:
The heat shield is divided into multiple panels with staggered joints instead of using a single-piece construction. This segmentation disrupts the continuous straight seams that cause airflow alignment, thereby reducing overheating and erosion while maintaining manufacturing feasibility through modular assembly.
Solution Approach 2:
The joints between panels are designed with asymmetric staggered patterns rather than symmetric or straight alignments. This asymmetry prevents uniform airflow paths along the seams, disrupting the harmful airflow alignment that leads to localized overheating and erosion.
2Object-affected harmful factors
If multiple heat resistant panels are used to form staggered joints, then airflow alignment is disrupted reducing overheating and erosion, but the system complexity increases
Solution Approach 1:
The heat shield is divided into multiple panels with staggered joints instead of using a single-piece construction. This segmentation disrupts the continuous straight seams that cause airflow alignment, thereby reducing overheating and erosion while maintaining manufacturing feasibility through modular assembly.
3Object-affected harmful factors
If panels are mated together with gaps filled with filler material, then joint erosion is reduced, but manufacturing precision requirements increase
Solution Approach 1:
The staggered joint design creates localized gap regions between panels that are filled with heat-resistant filler material. This local quality approach protects the joint areas from erosion while maintaining the overall staggered configuration, with the filler material providing the necessary seal and thermal protection at the joint locations.
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 staggered joint configuration effectively disrupts airflow alignment, reducing overheating and erosion of the filler material, thus enhancing the durability and effectiveness of the thermal protection system during high-temperature reentry.
Implementation Method 1
The lower surface of the spacecraft 100 is protected by a heat shield 102, which absorbs the thermal energy generated during deceleration of the spacecraft 100
Implementation Method 2
The first panel outer surface and second panel outer surface are configured for exposure to the atmosphere during reentry, while the inner surfaces protect the underlying structure
Implementation Method 3
The joint edges are deliberately shaped to be non-straight and non-uniform, reducing airflow alignment and erosion by creating gaps that are filled with a heat-resistant filler material
Implementation Method 4
reducing overheating and erosion of the filler material, thus enhancing the durability and effectiveness of the thermal protection system during high-temperature reentry
Data Source
AI summary
The thermal protection system disclosed herein is suitable for use with a spacecraft such as a reentry module or vehicle, where the spacecraft has a convex surface to be protected. An embodiment of the thermal protection system includes a plurality of heat resistant panels, each having an outer surface configured for exposure to atmosphere, an inner surface opposite the outer surface and configured for attachment to the convex surface of the spacecraft, and a joint edge defined between the outer surface and the inner surface. The joint edges of adjacent ones of the heat resistant panels are configured to mate with each other to form staggered joints that run between the peak of the convex surface and the base section of the convex surface.