Open-Back Spacecraft Platform Structure for Heat and Power Scaling
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Solution Overview
Problem
Existing spacecraft platform structures face inefficiencies in space utilization, heat dissipation, and power management, particularly for large payload antennas with high power consumption, which are challenging for satellite constellations.
Innovation Solution
A stackable, open-back spacecraft platform structure with a circular or polygonal primary support structure, including modules and secondary support frames, which allows for efficient heat dissipation and power transmission, and supports multiple spacecraft stacking.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a traditional single large box-like structure is used, then structural simplicity is maintained, but space utilization efficiency deteriorates and heat dissipation becomes challenging
Solution Approach 1:
The spacecraft platform is divided into multiple individual modules that can be stacked vertically. Each module contains sub-modules disposed within or on the individual module, allowing efficient use of launch vehicle fairing space while maintaining structural integrity through the open-back design that enables modular assembly and disassembly.
Solution Approach 2:
The platform transitions from a traditional single large box structure to a vertical stacking configuration. By utilizing the vertical dimension through multiple stacked modules, the design achieves higher space utilization efficiency within the launch fairing constraints while maintaining operational simplicity.
2Device complexity
If a traditional single large box-like structure is used, then structural simplicity is maintained, but heat dissipation capability deteriorates
Solution Approach 1:
The platform is segmented into multiple individual modules with open-back designs, creating multiple heat dissipation surfaces and pathways. This segmentation allows heat to be distributed across multiple modules rather than concentrated in a single large structure, improving overall heat dissipation capability.
Solution Approach 2:
The open-back design, which might initially appear to reduce structural integrity, actually provides beneficial heat dissipation surfaces. The exposed surfaces of the individual modules serve as effective radiators for heat dissipation, converting what could be seen as a structural weakness into a thermal management advantage.
3Power
If large payload antenna with high power consumption is used, then payload capacity is improved, but power management and heat dissipation become more challenging
Solution Approach 1:
The platform modules are designed with distributed power management capabilities, allowing each module to handle and dissipate heat from its associated payload equipment. This segmentation of power management functions reduces the overall complexity compared to a single centralized system while supporting high-power payloads.
Solution Approach 2:
The vertical stacking configuration provides multiple levels for power distribution and heat dissipation. By utilizing the vertical dimension, the system can route power and thermal management pathways through multiple modules, effectively handling the power requirements of large high-power antennas without excessive complexity.
4Volume of moving object
If stacking spacecraft atop one another is implemented, then space utilization efficiency is improved, but structural complexity and connection requirements increase
Solution Approach 1:
The individual modules are designed with universal connection interfaces that can accommodate various configurations and payloads. The open-back design provides standardized mounting structures that enable stacking of different spacecraft configurations while maintaining structural integrity, reducing the need for custom connection solutions.
Solution Approach 2:
The modular architecture with standardized interfaces allows for flexible stacking configurations. Each module can be independently designed and tested, then assembled into larger configurations, reducing overall structural complexity compared to monolithic designs while achieving high space utilization efficiency.
Data Source
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 including one or more individual modules, 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 including a first frame including at least four first frame members, each first frame member 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.