Monolithic Spacecraft Panel With Integrated Truss for Low Thermal Impedance
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Solution Overview
Problem
Conventional spacecraft panels made of composite sandwich structures face challenges such as high thermal impedance, high manufacturing costs, and labor intensity, with localized features requiring separate post-production attachment, and existing additive manufacturing methods struggle with unsupported features, warping, and cracking.
Innovation Solution
The development of additively manufactured spacecraft panels featuring a first and second skin connected by a truss structure, which are printed as a single unit, allowing for self-supporting truss members and integrated features like reinforcement, thermal management, and radiation shielding, reducing the need for post-processing and separate attachments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional composite sandwich-structure panels are used, then structural strength is improved, but thermal impedance increases and manufacturing cost increases
Solution Approach 1:
The patent merges the core structure and skin layers into a single additively manufactured unit, eliminating the need for separate bonding operations. This integration removes the bonding interfaces that create thermal impedance while maintaining the sandwich structure's mechanical strength, directly resolving the contradiction between strength and thermal performance.
Solution Approach 2:
The patent uses additively manufactured composite materials with integrated truss cores and skin layers that are bonded at the molecular level during the printing process. This creates a composite structure with superior thermal conductivity compared to conventionally bonded panels, while maintaining high structural strength through the optimized truss geometry.
2Strength
If conventional composite sandwich-structure panels are used, then structural strength is improved, but manufacturing time increases
Solution Approach 1:
The patent combines multiple manufacturing operations (core fabrication, skin fabrication, and bonding) into a single additive manufacturing process. The panel is printed as one continuous operation, eliminating the sequential steps required in conventional manufacturing and dramatically reducing production time while maintaining structural integrity.
Solution Approach 2:
The additive manufacturing process performs preliminary bonding actions during the printing itself, where each layer is bonded to the previous layer as it is deposited. This eliminates the need for separate post-manufacturing bonding operations and curing cycles, significantly accelerating production while ensuring structural strength.
3Strength
If conventional composite sandwich-structure panels are used, then structural strength is improved, but labor intensity increases
Solution Approach 1:
The patent merges multiple manual operations (core assembly, skin placement, bonding, and curing) into an automated additive manufacturing process. The system requires minimal human intervention beyond initial setup and parameter configuration, dramatically reducing labor intensity while producing panels with consistent structural strength through computer-controlled manufacturing.
Solution Approach 2:
The additive manufacturing system performs self-service by automatically depositing and bonding materials layer by layer without human intervention. The process includes self-aligned positioning, self-controlled bonding, and self-monitoring of manufacturing parameters, eliminating the need for manual labor in core placement, skin attachment, and bonding operations while maintaining high structural quality.
4Adaptability or versatility
If separate parts are attached post-production for localized features, then functional requirements are met, but manufacturing cost increases
Solution Approach 1:
The patent merges localized functional features (such as radiation shielding, thermal management elements, and reinforcement) directly into the panel structure during additive manufacturing. These features are printed as integral parts of the panel rather than separate components, eliminating the need for post-production attachment operations and reducing overall manufacturing cost while maintaining design versatility.
Solution Approach 2:
The additive manufacturing process enables local quality by allowing different materials, densities, or structural configurations to be printed in specific regions of the panel. Localized features such as reinforced zones, thermal management channels, or radiation shielding layers can be precisely placed where needed during the printing process, providing functional adaptability without the cost of separate part attachment.
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
This approach enhances thermal performance, reduces manufacturing time and costs, and integrates functional features like shielding and reinforcement within a single, monolithic structure, improving the efficiency and effectiveness of spacecraft panels in space environments.
Implementation Method 1
selective laser melting (SLM)
Implementation Method 2
direct metal laser sintering (DMLS)
Implementation Method 3
selective laser sintering (SLS)
Implementation Method 4
fused deposition modelling (FDM)
Implementation Method 5
electron beam melting (EBM)
Data Source
AI summary
A spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.