Flat Modular Space Platform for Thermal and Attitude Stability
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Solution Overview
Problem
Existing orbital structures, such as the ISS-type architecture, face limitations in mass optimization, controllability, and attitude control due to significant dimensions, particularly in terms of heat dissipation and flexure under solar radiation, making them unsuitable for expanding functionalities.
Innovation Solution
A space module composed of identical, flat-shaped elements with solar panels and radiators, arranged in specific planes to optimize mass distribution and orientation, allowing for a deployable space platform with self-sufficiency in energy and heat dissipation, and controlled by a robot or mass displacement for attitude control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If ISS-type centralized architecture is used, then functional integration is achieved, but mass optimization deteriorates and distance between functions increases causing heat dissipation losses
Solution Approach 1:
The space platform is divided into multiple autonomous modular units, each capable of independent operation with its own power generation and heat dissipation systems. This segmentation eliminates long-distance energy and thermal transfer, reducing heat dissipation losses while maintaining functional integration across the distributed platform.
Solution Approach 2:
Each modular unit is designed with localized power generation (solar panels) and localized heat dissipation (radiators), creating self-sufficient functional units. This local quality approach ensures that each module can operate independently and optimizes thermal management by eliminating long-distance heat transfer through the structure.
2Adaptability or versatility
If large dimensions are used to provide additional functions, then functional versatility is improved, but controllability and attitude control deteriorate due to significant flexure under solar radiation
Solution Approach 1:
The large-scale platform is segmented into multiple small modular units that can be independently controlled. This segmentation reduces the flexure and deformation of individual modules under solar radiation pressure, while the collective arrangement of modules provides the required large dimensions for diverse functions.
Solution Approach 2:
The modular architecture allows dynamic reconfiguration of the platform by adding, removing, or repositioning individual modules. This dynamic capability enables the platform to adapt to different functional requirements while maintaining structural integrity and attitude control through distributed actuation across multiple small modules rather than one large structure.
3Reliability
If CMG-type actuators are used for attitude control, then attitude controllability is improved, but mass increases significantly
Solution Approach 1:
Instead of using one or two large CMG actuators, the attitude control function is segmented and distributed across multiple small modular units, each equipped with its own small reaction wheels or control moment gyroscopes. This segmentation reduces the mass of individual actuators while maintaining overall platform controllability through coordinated operation of multiple distributed actuators.
Solution Approach 2:
The patent explores replacing traditional mechanical CMG actuators with alternative control mechanisms such as magnetorquers or distributed small reaction wheels that have lower mass. This substitution reduces the overall mass dedicated to attitude control while maintaining effective controllability through the distributed architecture.
4Reliability
If propellants are used for attitude control, then attitude controllability is improved, but propellant consumption occurs continuously
Solution Approach 1:
The attitude control function is distributed across multiple modular units, each with its own small propellant tanks and thrusters. This segmentation allows for highly efficient propellant usage by only activating the minimum necessary thrusters for small attitude adjustments, rather than relying on a single large propellant system that must maintain continuous readiness.
Solution Approach 2:
Each modular unit is self-sufficient in attitude control, with its own small propellant reserve and control actuators. This self-service capability allows individual modules to perform local attitude adjustments without consuming propellant from a centralized system, reducing overall propellant consumption through distributed, on-demand control.
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
The solution enables scalable, controllable, and efficient space platforms with reduced mass and energy consumption, minimizing heat loss and structural stress, while maintaining optimal operational conditions for solar panels and radiators.
Implementation Method 1
The type of each element is chosen from the group comprising: solar panel
Implementation Method 2
a plurality of radiators arranged in a second plane perpendicular to the first plane; preferably, the second plane being intended to be aligned with the Earth's nadir
Data Source
Figure 1
Figure 2
Figure 3A~3B
AI summary
The present invention relates to a space module (20) intended to be deployed in space to form a space platform (10), the space module (20) being formed of a predetermined number of elements (21, 22, 23) all having the same flat shape in an extension plane (P1, P2) of the corresponding element (21, 22, 23), each element (21, 22, 23) being of a predetermined type, at least one element (21, 22, 23) forming a payload (21).