Elongated Space Platform Attitude Control With Movable Mass Modules
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Solution Overview
Problem
Existing orbital structures, such as the ISS-type architecture, face limitations in controllability and mass optimization due to significant dimensions, leading to issues like heat dissipation and attitude control difficulties, especially when scaling up.
Innovation Solution
A method for piloting an elongated space platform using active and passive attitude control, involving displacement of mass on a control surface and actuation of actuators/propulsors, with a modular design of identical space modules that are self-sufficient in energy and heat dissipation, and a robot for deployment and maintenance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the dimensions of the space platform are increased to provide additional functions, then the platform's functionality and capacity are improved, but the controllability and attitude control become more difficult
Solution Approach 1:
The space platform is divided into multiple independent modules (e.g., accommodation module, experimentation module, observation module) that can be assembled in various configurations. Each module has its own control capabilities, allowing the platform to maintain controllability even as it scales in size and functionality through modular addition rather than monolithic expansion.
Solution Approach 2:
The platform employs deployable structures and movable components that allow it to dynamically adjust its configuration and control characteristics. This enables the platform to optimize its attitude control properties based on its current operational state and dimensional configuration, maintaining reliability as it transitions between different functional states.
2Device complexity
If a centralized functional architecture is used to control the platform, then the control system is simplified, but the mass increases and heat dissipation losses occur
Solution Approach 1:
The control system is segmented and distributed across multiple modules rather than centralized in one location. Each module has localized control capabilities, reducing the mass of any single control component and minimizing heat dissipation distances. This distributed architecture maintains overall system simplicity while reducing total mass and thermal losses.
Solution Approach 2:
Each module is designed with localized control functions appropriate to its specific operational requirements, rather than relying on a centralized control system. This reduces the mass of control components by placing only necessary control elements at each location, and minimizes heat dissipation by reducing the distance between heat-generating components and their local control systems.
3Adaptability or versatility
If the platform dimensions are increased, then the capacity for functions is improved, but the distance between different functions increases leading to heat dissipation losses
Solution Approach 1:
The platform is segmented into functional modules that are positioned to minimize heat dissipation losses. By distributing functions across modular units with localized thermal management, the system maintains functional capacity over larger dimensions while reducing the energy loss associated with heat transfer over long distances.
Solution Approach 2:
The platform utilizes three-dimensional spatial arrangement of modules to optimize thermal management. By arranging functional modules in a three-dimensional configuration rather than linear extension, the platform maintains functional capacity while reducing the average distance between thermally coupled components, thereby minimizing heat dissipation losses.
4Adaptability or versatility
If large dimensions are used to provide additional functions, then the platform's capability is improved, but structural flexures increase due to solar radiation
Solution Approach 1:
The platform structure is segmented into multiple rigid modules connected by flexible joints or struts. This segmentation allows each module to maintain its own structural stability against solar radiation pressure, while the modular connections accommodate dimensional changes without compromising overall structural integrity. The segmented design reduces structural flexures by distributing thermal and radiative loads across multiple independent structural units.
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
Enables easy expansion of space platform dimensions while ensuring controllability, optimizing space and mass, reducing the need for propellants, and minimizing structural stresses and losses, with modular, deployable, and self-sufficient modules.
Implementation Method 1
passive attitude control by the Earth's gradient
Data Source
Figure 1
Figure 2
Figure 3A~3B
AI summary
The present invention relates to a method for piloting an elongated space platform along a platform axis, the method comprising an active attitude control phase of the platform by displacement (110) of a mass on a control surface of the platform, the control surface extending along the platform axis.