Modular Solar Array for Spacecraft Energy Supply
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Solution Overview
Problem
Current aerospace applications face challenges in accommodating solar arrays and other components within launcher systems due to space restrictions, requiring complex and costly tailoring processes that limit satellite design options and cannot adapt to changing power needs post-launch.
Innovation Solution
A modular and scalable energy supplying device comprising multiple solar panel units that can be automatically assembled and configured in space, using coupling members to connect with satellites, allowing for independent deployment and adjustment based on operational requirements without manned support.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If solar arrays are fixedly attached to satellites prior to launch, then energy supply is guaranteed, but space restrictions within the launcher system increase and design flexibility is reduced
Solution Approach 1:
The solar array system is divided into modular solar array units that can be independently configured and attached to the satellite after launch. Each unit can be separately deployed and positioned, allowing flexible adaptation to different satellite designs and power requirements without compromising the reliability of energy supply.
Solution Approach 2:
The solar array configuration is made dynamic and adjustable after launch rather than being fixed beforehand. The modular units can be repositioned, reconfigured, or replaced in space to adapt to changing power needs or mission requirements, while still ensuring continuous energy supply to the satellite.
2Power
If solar array dimensions are increased to meet higher power needs, then power supply capability is improved, but available space within the launcher system is reduced
Solution Approach 1:
The solar array is segmented into multiple modular units that can be independently launched and deployed. This allows the satellite to start with a compact configuration that fits within launcher constraints, then expand power capacity by adding or deploying additional modules in space as needed.
Solution Approach 2:
The modular solar array units are designed to be compactly stowed within the launcher system during launch, nested in a space-efficient manner. After deployment in space, these same units can be expanded and configured to provide the required power output, effectively transforming from a compact launch configuration to an expanded operational configuration.
3Volume of moving object
If complex stowing solutions are implemented to accommodate solar arrays, then space utilization within the launcher system is optimized, but device complexity and tailoring costs increase
Solution Approach 1:
By segmenting the solar array into standardized modular units, the complexity of designing custom stowing solutions for each satellite is reduced. The modular design allows for通用的 launch integration approaches that can accommodate different power requirements without requiring complex tailoring for each mission.
Solution Approach 2:
The modular solar array units are designed with universal interfaces and standardized configurations that can be adapted to different satellite types and launcher systems. This universality eliminates the need for complex, mission-specific tailoring processes while maintaining efficient space utilization within the launcher.
4Manufacturing precision
If tailoring processes are performed prior to launch, then space constraints are addressed, but adaptability to changing power needs after launch is lost
Solution Approach 1:
The modular solar array units are prepared and qualified beforehand for launch, ensuring they meet all technical requirements. However, their final configuration and assembly are deferred until after launch, allowing the system to maintain manufacturing precision during production while gaining the flexibility to adapt configurations in space based on actual mission needs.
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 solution enables efficient use of launcher space, enhances satellite design flexibility, and allows for dynamic power adjustments, eliminating the need for pre-launch tailoring and reducing costs associated with launch and assembly processes.
Implementation Method 1
a plurality of solar panel units (14) configured to convert received light into electrical energy
Data Source
Figure 1
Figure 2
AI summary
The present disclosure generally relates to the field of energy supply in aerospace applications. More particularly, the present disclosure relates to a method for coupling an energy supplying device to an energy consuming device in space and to a system including an energy supplying device, an energy consuming device and a mobile assembly unit residing in space. According to an embodiment, the energy supplying device is operable in space and comprises: a plurality of solar panel units configured to convert received light into electrical energy, a plurality of first coupling members configured to couple the plurality of solar panel units with each other, and a second coupling member configured to electrically couple the energy supplying device with the energy consuming device. The energy supplying device is further configured to supply electrical energy to the energy consuming device in space. A configuration of the plurality of solar panel units is changeable in space according to an operational requirement of the energy consuming device.