Deployable Space Reflector With Double-Convex Tensioning Framework
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Solution Overview
Problem
Existing deployable space reflectors suffer from low stiffness and stability, complex deployment, large stowed package height, and limited deployed size due to the use of tensioning frameworks with double concave lens shapes.
Innovation Solution
A deployable space reflector design featuring a peripheral support framework with hinged full cross-rods and trapeze-shaped bays, combined with a tensioning framework that forms double convex lens surfaces, and a deployment mechanism using rollers and cables, to enhance stiffness, stability, and reduce stowed package height.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Shape
If a tensioning framework with double concave lens shape is used, then the reflecting surface can be shaped, but the stowed package height becomes large
Solution Approach 1:
The patent inverts the traditional double concave lens shape to a double convex lens shape for the tensioning framework. This inversion allows the framework to achieve the necessary surface shaping function while significantly reducing the stowed package height, as the convex configuration folds more compactly while maintaining structural integrity and optical performance.
Solution Approach 2:
The patent changes the geometric parameters of the tensioning framework from a double concave lens configuration to a double convex lens configuration. This parameter change fundamentally alters the folding behavior and stowed height while preserving the ability to shape the reflecting surface, thereby resolving the contradiction between shaping capability and compact storage.
2Ease of manufacture
If rectangular ring facets are used in the peripheral support framework, then the structure can be assembled, but additional stiffening means are required
Solution Approach 1:
The patent segments the peripheral support framework into triangular facets instead of rectangular ones. Each triangular facet is a self-stiffening unit that inherently resists deformation, eliminating the need for additional diagonal stiffening rods or cables. This segmentation approach maintains assembly simplicity while providing inherent structural stiffness.
Solution Approach 2:
The patent introduces curvature to the framework structure by using triangular facets that form a curved or conical overall shape. This curvature provides natural structural stiffness and stability to the framework, reducing the need for additional straight-line stiffening elements while maintaining the deployable nature of the structure.
3Duration of action of moving object
If V-fold rods are used in the peripheral framework, then the structure can fold, but the deployment complexity increases
Solution Approach 1:
The patent divides the peripheral framework into multiple triangular facets with simple hinge connections, replacing the complex V-fold rod mechanism. Each triangular unit can fold and deploy independently through simple hinge rotations, significantly reducing the overall deployment complexity while maintaining the folding capability necessary for space deployment.
4Volume of moving object
If the stowed package height is reduced, then the launch efficiency improves, but the deployed size is limited
Solution Approach 1:
By inverting the tensioning framework from double concave to double convex configuration, the patent achieves a more compact stowed height while the convex shape provides better mechanical leverage for achieving larger deployed dimensions. The inverted configuration allows the structure to expand more effectively from a compact base.
Solution Approach 2:
The patent employs a multi-dimensional deployment strategy where the framework expands not only radially but also vertically through the hinge mechanisms of the triangular facets. This multi-dimensional expansion allows the structure to achieve large deployed sizes from a compact stowed configuration, overcoming the limitation of single-dimensional expansion.
Data Source
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AI summary
The present invention relates to radio technique, namely to space structures, for example, large deployable space reflectors (symmetric, asymmetric, offset and other type of reflectors), radio and optical telescopes, sun-concentrators and other structures with analogous purpose. Advantages of this invention are in increasing deployed stiffness and stability, as well as in increasing reliability of deployment, achieving large deployed seized high accuracy of reflector realization and in decreasing height of the stowed package of the reflector.