Mesh Reflector with Truss Structure for Space Antennas
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing reflector assemblies for spacecraft and antennas face challenges in achieving a lightweight, durable, and precisely shaped structure that can be compactly stowed for transportation and autonomously deployed in space while maintaining high reflectivity and structural integrity under environmental stresses.
Innovation Solution
A reflector assembly featuring a collapsible frame with interconnected curved net bodies, tensioning members, and a support structure that secures a reflective mesh into a precise, curved shape, allowing for compact deployment and expansion, and utilizing uniaxial fiber composite materials for strength and lightness.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If a rigid, deployable outer support rim and curved frame net are used to maintain reflector surface shape accuracy, then the reflector can achieve desired RF or light reflection requirements, but the overall weight and structural complexity increase
Solution Approach 1:
The patent uses a flexible reflective mesh membrane instead of rigid reflector surfaces. The mesh is tensioned between two geodesic dome structures to achieve the desired parabolic shape, eliminating the need for heavy rigid support structures while maintaining surface accuracy for RF reflection
Solution Approach 2:
The patent employs composite construction combining the reflective mesh with the geodesic dome truss structures. This composite approach distributes structural loads efficiently through the dome geometry while keeping individual components lightweight, resolving the contradiction between structural integrity and weight
2Weight of moving object
If the reflector assembly is designed to be lightweight and compact for space transportation, then launch efficiency improves, but structural integrity and durability under space environmental stresses may be compromised
Solution Approach 1:
The patent divides the reflector into two separate geodesic dome structures (inner and outer domes) connected by struts and tensioning cables. This segmentation allows each component to be optimized independently for weight and strength, while the assembled structure provides the required structural integrity to withstand space environmental stresses
Solution Approach 2:
The tensioning cables and strut system automatically maintain the reflector's structural integrity through pre-tensioning and geometric stability. The structure self-adjusts to maintain its shape and resist external forces without requiring active control systems or heavy reinforcement, achieving reliability through passive structural design
3Volume of moving object
If the reflector assembly is designed for compact stowage during transportation, then launch package size is reduced, but deployment complexity and potential for shape distortion increase
Solution Approach 1:
The patent employs deployable geodesic dome structures that can transition from a compact stowed configuration to a fully deployed operational configuration. The dome struts and cables are designed to articulate and extend during deployment, allowing the large-aperture reflector to be transported in a compact form factor while maintaining structural integrity during the transition
Solution Approach 2:
The geodesic dome geometry provides inherent structural stability and efficient packing characteristics. The curved, spherical-based structure allows for compact stowage while the geometric rigidity of the dome framework ensures accurate deployment and maintains the parabolic reflector shape, reducing complexity compared to alternative deployment mechanisms
4Area of moving object
If a large-aperture reflector is deployed in space, then RF signal collection capability improves, but the structure becomes more vulnerable to environmental stresses and shape distortion
Solution Approach 1:
The large-aperture reflector is segmented into two geodesic dome structures rather than using a single monolithic surface. This segmentation distributes the structural loads from environmental stresses across multiple smaller elements, reducing the vulnerability of any single point while maintaining the large overall aperture area for RF signal collection
Solution Approach 2:
The patent uses a composite structure combining the reflective mesh with the geodesic dome framework. This composite design allows the thin, lightweight mesh to achieve large aperture area while the dome truss structure provides the necessary strength and stiffness to resist space environmental stresses, preventing shape distortion of the reflective surface
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 a lightweight, compact, and precisely shaped reflector assembly that maintains high reflectivity and structural integrity, minimizing antenna gain loss and facilitating efficient deployment and operation in space environments.
Implementation Method 1
A reflective mesh is secured to the first body for receiving and reflecting electromagnetic signals
Data Source
Figure 1~2
Figure 3
Figure 4~5
AI summary
A reflector assembly includes a frame centered about a longitudinal axis, a first curved body extending from the frame, and a second curved body extending from the frame and connected to the first curved body for supporting the first curved body. A reflective mesh has an electromagnetically reflective surface and a support structure secures the reflective mesh to the first curved body and spaces the reflective mesh away from the first body towards the second body.