Open-Back Spacecraft Platform Structure for Stacked Thermal Management
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Solution Overview
Problem
Existing spacecraft platform structures for satellite constellations face inefficiencies in space utilization, heat dissipation, and power management, particularly for large payload antennas with high power consumption, which traditional single-box designs struggle to address effectively.
Innovation Solution
A stackable, open-back spacecraft platform structure with a circular or polygonal primary support structure, including individual modules and a secondary support structure, which facilitates heat dissipation through an open back design and allows for efficient stacking and connectivity of multiple spacecraft, optimizing power generation and payload capacity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a traditional single large box-like structure is provided as a spacecraft, then structural simplicity is maintained, but space utilization efficiency deteriorates and heat dissipation capability is insufficient
Solution Approach 1:
The spacecraft platform is divided into multiple individual modules that can be stacked vertically. Each module contains subsystems and can be independently assembled, allowing efficient use of launch vehicle fairing space while maintaining structural simplicity through modular design
Solution Approach 2:
The platform transitions from a single horizontal box structure to a vertical stacked configuration. By utilizing the vertical dimension, multiple spacecraft can be stacked atop one another, significantly improving space utilization efficiency within the launch fairing
2Ease of manufacture
If a traditional single large box-like structure is provided as a spacecraft, then manufacturing simplicity is maintained, but heat dissipation capability deteriorates
Solution Approach 1:
The platform is segmented into multiple modules with open-back designs that expose thermal pathways. This segmentation allows heat to be dissipated through multiple surfaces and pathways rather than being confined within a single enclosed box structure
Solution Approach 2:
The back portion of each module is designed as an open structure rather than a closed wall. This extraction of the back wall element creates thermal pathways and radiation surfaces that significantly enhance heat dissipation capability while maintaining manufacturing simplicity through standardized module designs
3Volume of moving object
If spacecraft are stacked atop one another to improve space efficiency, then space utilization is improved, but power management and connectivity complexity increases
Solution Approach 1:
The module connectors are designed with multi-functionality, serving as both mechanical attachment points for stacking and as interfaces for power and data transmission. This universal design simplifies the overall system by combining multiple functions into a single component, reducing connectivity complexity despite the stacked configuration
4Area of moving object
If D2D constellation antennas with very large aperture are implemented, then payload capacity is improved, but power consumption and heat generation increase
Solution Approach 1:
The back of each module is designed as an open structure to create thermal pathways and radiation surfaces. This extraction of the back wall enables efficient heat dissipation from the high-power antenna systems, allowing large aperture antennas to operate effectively without excessive heat accumulation
Solution Approach 2:
The vertical stacking configuration utilizes the vertical dimension to separate thermal pathways and radiation surfaces. By stacking modules vertically with open-back designs, heat can be dissipated through multiple vertical pathways and radiation surfaces, effectively managing the thermal load of high-power antenna systems
Data Source
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Figure 2A
AI summary
A system for an open-back spacecraft platform structure, a method of assembling a primary platform structure of an open-back spacecraft platform, and a method of assembling a system including an open-back spacecraft platform structure are provided. The system includes the spacecraft platform structure including a circular or polygonal primary support structure (102) including one or more individual modules (102), each individual module including sub-modules disposed within or on the individual module, each individual module being all or part of a side of the circular or polygonal primary support structure and defining an open back of the spacecraft platform structure, a secondary support structure (105) including a first frame including at least four first frame members (110,111), each first frame member (110,111) connected to the primary support structure via a first fitting and connected to the other frame members, and one or more module connectors for bearing and/or transmitting loads of the open-back spacecraft platform structure.