Self-Deploying Satellite Structure Using Curved Panels
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing deployable structures for space applications, such as antennas and photovoltaic panels, face challenges with high mass and cost due to external deployment mechanisms, and compatibility issues with structures that require edge-to-edge panel alignment, while also needing improved reliability and mechanical stress resistance.
Innovation Solution
A self-deployable structure using panels with inherent curvature and flexible links that store elastic deformation energy, where compression links assist in spontaneous deployment by releasing stored energy and maintaining panel alignment through traction and alignment links, minimizing mass and bulk.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If external driving elements (motorization, cables) are used to deploy the structure, then the structure can be deployed reliably, but the mass and cost of the structure increase significantly
Solution Approach 1:
The structure utilizes its own elastic prestress energy to drive deployment automatically. The panels return to their natural arched shape after folding, and this elastic recovery force is harnessed to drive the deployment mechanism without requiring external motors or cables, thereby eliminating the need for heavy external driving elements while maintaining reliable deployment
Solution Approach 2:
The panels are pre-curved during manufacturing to have a natural arched shape. This preliminary geometric configuration stores elastic potential energy that is later released during deployment. The clamping means are pre-installed to maintain the folded state, and their release automatically triggers the stored energy to drive deployment
2Stability of the object's composition
If clamping means are used to maintain elastic prestress in folded panels, then the panels can be kept in folded position, but the deployment mechanism becomes more complex and heavier
Solution Approach 1:
The deployment function is extracted from external driving elements and transferred to the inherent elastic prestress of the panels themselves. The clamping means are simplified to merely hold the folded position, while the elastic recovery force performs the deployment work, separating the holding function from the driving function
Solution Approach 2:
The structure uses its own elastic prestress to drive deployment, making the system self-sufficient. The panels' natural tendency to return to their arched shape provides the driving force, eliminating the need for complex external motorization or cable systems
3Extent of automation
If Carpentier joints (curved elastic strips) are used for folding, then spontaneous deployment is possible, but the structure cannot maintain edge-to-edge panel alignment in deployed position
Solution Approach 1:
The connection between panels is segmented into multiple functional elements: curved elastic strips for spontaneous deployment, rigid links for maintaining edge-to-edge alignment, and clamping means for securing the folded position. This segmentation allows each element to perform its specific function without compromising the others
Solution Approach 2:
The invention combines multiple connection mechanisms (curved elastic strips, rigid links, clamping means) into a unified hinge assembly that integrates both spontaneous deployment capability and precise alignment maintenance. The curved elastic strips and rigid links work together in the same hinge to achieve both functions simultaneously
4Extent of automation
If panels are made with inherent curvature for elastic prestress, then spontaneous deployment is enabled, but the structure's resistance to mechanical stresses may be compromised
Solution Approach 1:
The structure transitions from a static rigid configuration to a dynamic system that can adapt its stiffness. In the folded state, the panels are constrained by clamping means, providing structural rigidity. During deployment, the panels dynamically return to their natural arched shape, utilizing elastic prestress. In the deployed state, the natural curvature provides both structural integrity and stress resistance
Solution Approach 2:
The hinge assembly uses composite construction combining curved elastic strips (for flexibility and energy storage) with rigid links (for structural strength and alignment). This composite approach allows the structure to simultaneously achieve spontaneous deployment capability and mechanical stress resistance through the synergistic combination of different material properties
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 structure achieves spontaneous deployment with reduced mass and cost, enhanced reliability, and improved mechanical stress resistance, allowing for efficient and precise panel alignment and deployment, while maintaining structural integrity under various loads.
Implementation Method 1
flexible links that store elastic deformation energy
Implementation Method 2
panels have a natural curvature at rest, said curvature being flattened by clamping means maintaining an elastic prestress
Data Source
Figure 1~4
Figure 5~7
AI summary
The invention relates to a self-deploying deployable structure (1) comprising at least two adjacent hinged panels (2), each panel having a non-planar surface at rest. The structure is adapted to be placed in a folded position in which the panels are folded over each other and held flat by compression and elastic deformation of their curvature, or in a deployed position in which the panels are aligned edge to edge along their adjoining edges and extending from one another. A flexible link (7) connecting the adjoining edges of the panels comprises at least a first tension link (4) holding the panels edge to edge in the deployed position, and at least a second compression link (5) adapted to be pressed against the outer faces of the panels and having a length suitable for the compression link to remain under tension as long as elastic deformation of the panels persists.The flexible link (7) further includes at least one alignment link (6) adapted to prevent lateral displacement of the panels relative to each other. The deployable structure is adapted to form solar panels and/or antennas for satellites in space, particularly for microsatellites.