Modular Space Platform Layout for Propellant-Free Attitude Control
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Solution Overview
Problem
Existing orbital structures, such as the ISS, face limitations in controllability and mass optimization due to centralized, functional designs, especially when dimensions increase, leading to attitude control difficulties and significant flexure issues.
Innovation Solution
A space platform composed of identical, self-sufficient space modules with a homogeneous mass distribution, each equipped with solar panels and radiators, forming a structure that can be easily expanded and controlled using a robot or movable mass for attitude control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If CMG-type actuators are used to control the attitude of the structure, then attitude control is achieved, but the mass of the system increases significantly
Solution Approach 1:
The space platform is divided into multiple identical modules, each with its own solar panels and radiators. This segmentation allows distributed mass distribution that naturally provides attitude control stability, reducing the need for heavy centralized actuators like CMGs.
Solution Approach 2:
The patent employs a moving mass mechanism where a movable mass can shift position along the platform structure to dynamically adjust the center of mass and control attitude. This dynamic approach replaces static heavy actuators with a lighter, movable mass system that achieves the same control function.
2Ease of operation
If propellants are used for attitude control, then attitude control is achieved, but propellant consumption occurs
Solution Approach 1:
The movable mass mechanism provides a propellant-free attitude control method. By shifting the movable mass along the platform structure, attitude control is achieved through mechanical rebalancing rather than propellant consumption, eliminating the harmful substance loss entirely.
3Adaptability or versatility
If the dimensions of the space platform are increased to provide additional functions, then functional versatility is improved, but controllability and mass optimization become more difficult
Solution Approach 1:
The platform is composed of multiple identical modules that can be easily added or removed to change the overall dimensions and functionality. This modular segmentation maintains mass distribution characteristics and control properties regardless of the number of modules, simplifying controllability and mass optimization even as the platform grows.
Solution Approach 2:
Each module is designed with specific local characteristics (solar panels for power, radiators for thermal control) that are optimally positioned within each module. This local optimization ensures that as modules are added to increase dimensions, each local unit maintains optimal mass distribution and functional efficiency, preventing overall system complexity from becoming unmanageable.
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 efficient attitude control and mass optimization, minimizing structural stresses and losses while allowing easy expansion and deployment, reducing the need for heavy actuators and propellants.
Implementation Method 1
each space module comprises a payload and is self-sufficient in energy and heat dissipation; each module comprises a plurality of solar panels forming a foreground of the corresponding module
Implementation Method 2
each space module comprises a payload and is self-sufficient in energy and heat dissipation; the module comprising a plurality of radiators arranged in a second plane perpendicular to the first plane
Data Source
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AI summary
The present invention relates to a space platform (10) formed of a plurality of identical space modules (20) assembled together to form an elongated structure along a platform axis (X), said structure having a substantially homogeneous mass distribution along the platform axis (X).