Modular Spacecraft Panels for Heat Dissipation and Fault Tolerance
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Solution Overview
Problem
Spacecraft design faces challenges in accommodating propellant tanks and electrical equipment due to size constraints, leading to inefficient heat dissipation and potential temperature issues, especially when propellant tanks have a flat shape, which can hinder the layout of satellite payload compartments.
Innovation Solution
A spacecraft system comprising identically configured panels networked together via a communications bus, allowing for resource sharing and autonomous control of mission objectives, including power and thruster fuel management, to achieve cooperative mission objectives without a central control system.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If horizontally-stacked mounting panels are used above a flat propellant tank, then equipment space is provided, but heat dissipation efficiency deteriorates and temperature control becomes difficult
Solution Approach 1:
The patent transitions from horizontal stacking to vertical stacking of mounting panels, utilizing the vertical dimension above the propellant tank. This dimensional change allows heat to dissipate more effectively in the vertical direction while maintaining equipment accommodation space, resolving the contradiction between equipment space provision and heat dissipation efficiency.
2Volume of moving object
If a flat propellant tank design is used, then size requirements are met, but payload compartment layout flexibility deteriorates
Solution Approach 1:
The patent segments the spacecraft structure into modular components: the flat propellant tank as a base unit and multiple mounting panels as separate, stackable units. This segmentation allows the payload compartment layout to be flexibly configured by stacking panels in different arrangements while maintaining the space-efficient flat tank design, thus preserving both size requirements compliance and layout flexibility.
3Ease of operation
If centrally-controlled architecture is used, then coordination is simplified, but system complexity and manufacturing costs increase
Solution Approach 1:
The patent implements a distributed control architecture where each mounting panel operates autonomously with its own controller, eliminating the need for a centralized control system. Each panel self-manages its functions and coordinates with neighboring panels through direct communication, reducing overall system complexity and manufacturing costs while maintaining effective coordination through decentralized decision-making.
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 modular design enhances efficiency, reduces manufacturing time and costs, provides redundancy, and ensures fault tolerance, allowing the spacecraft to complete mission objectives even if individual panels fail, while efficiently managing resources and heat dissipation.
Implementation Method 1
at least one solar panel configured to convert solar energy into power
Data Source
AI summary
One embodiment of the invention includes a spacecraft system. The system includes a spacecraft payload system coupled to a spacecraft frame. The system also includes a plurality of spacecraft panels disposed about the spacecraft frame. Each of the plurality of spacecraft panels can be communicatively coupled together via a network and configured substantially identically with respect to each other, and can include a processor and associated spacecraft control components. The processors of each of the spacecraft panels controlling the respective spacecraft control components independently to cooperatively and autonomously implement spacecraft control functions to implement a common mission objective.