Deployable Reflector Antenna Ring for Stable Low-Volume Unfolding
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Solution Overview
Problem
Conventional deployable reflector antennas for space applications face challenges with structural complexity, weight, assembly difficulty, mechanical instability, and misalignment during deployment, particularly in space environments, and require improved structural integrity and reliable unfolding mechanisms.
Innovation Solution
A deployable symmetrical reflector antenna design using single-axis cylindrical joints, pantographic rings on spherical surfaces, and a hybrid composition of rigid rods and tensioned cables to form a tensegrity-like system with a concave parabolic and convex hyperbolic mesh, enabling consistent deployment and reduced weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If conventional rigid mechanical components or membrane-based surfaces are used for deployable reflector antennas, then compact stowage is achieved, but structural integrity and alignment stability deteriorate during deployment
Solution Approach 1:
The reflector surface is segmented into multiple rigid panels that can be independently positioned and secured. This segmentation allows the structure to be folded into compact volumes for stowage while maintaining structural integrity when deployed, as each panel can be precisely positioned and locked in place without relying on the flexibility of membrane materials.
Solution Approach 2:
The deployable reflector antenna employs a nested folding mechanism where panels and support structures are arranged to fold concentrically into a compact cylindrical volume. The rigid panels nest within each other during stowage, achieving minimal volume while preserving the ability to reconstruct the full reflective surface geometry during deployment through controlled unfolding sequences.
2Reliability
If complex mechanical components are used to achieve reliable deployment, then deployment reliability improves, but device complexity and weight increase
Solution Approach 1:
Complex actuation mechanisms are extracted and replaced with simpler deployment systems. The reflector panels utilize passive deployment mechanisms where gravitational forces and minimal actuation forces suffice to unfold the nested structure, eliminating the need for complex motors, sensors, and control systems that would increase device complexity and weight while compromising reliability.
Solution Approach 2:
The deployment mechanism transitions from static, heavily actuated systems to dynamic, motion-based deployment. The nested panels are designed to unfold through controlled motion sequences where the movement itself creates the necessary alignment and tension, reducing the need for complex mechanical components while maintaining deployment reliability through kinematic design.
3Stability of the object's composition
If rigid structures are used to maintain shape, then structural stability improves, but weight increases
Solution Approach 1:
Rigid structural properties are applied locally only where necessary to maintain reflector shape accuracy, rather than throughout the entire structure. The rigid panels are positioned at critical locations where shape stability is most important for maintaining reflective geometry, while other portions of the structure use lighter, more flexible materials that reduce overall weight without compromising essential shape stability.
Solution Approach 2:
The reflector structure employs composite construction combining rigid panels with lighter support frameworks. The rigid panels provide local shape stability where needed for accurate signal reflection, while the supporting structure uses high-strength-to-weight ratio materials that maintain overall structural integrity without the excessive weight of fully rigid construction.
4Volume of moving object
If traditional folding mechanisms are used for compact stowage, then stowage volume reduces, but misalignment and deformation occur during deployment
Solution Approach 1:
Alignment features and positioning mechanisms are pre-configured into the rigid panels and support structures before deployment. The panels include built-in alignment references and mechanical constraints that guide them into precise positions during the unfolding sequence, eliminating misalignment issues that plague traditional folding mechanisms. This preliminary preparation ensures that when the structure deploys, components automatically assume their correct relative positions.
Solution Approach 2:
Traditional mechanical folding joints that rely on friction and contact wear are replaced with alignment-based positioning systems. The rigid panels use geometric constraints and precision-machined interfaces that maintain alignment through their inherent geometry rather than through mechanical friction or deformation-resistant materials, achieving superior alignment precision without the complexity of advanced mechanical joint designs.
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 design achieves reliable, lightweight, and geometrically stable deployment with reduced stowage volume, facilitating smooth integration with spacecraft platforms and maintaining reflective accuracy.
Implementation Method 1
The deployable ring includes a plurality of torsion springs configured to bias the deployable ring towards an open position. At least one of the plurality of torsion springs is coupled to one or more joints of the plurality of joints.
Implementation Method 2
The deployable ring includes a plurality of tension cables. A tension cable of the plurality of tension cables connects a first joint and a second joint positioned within the same tier.
Data Source
AI summary
A deployable reflector antenna is provided. An example antenna includes a deployable ring including a plurality of internal combined arms, a plurality of external combined arms, and a plurality of joints arranged circumferentially in a predetermined number of tiers from a bottom of the deployable ring to a top of the deployable ring. Each of the plurality of joints connects, in a scissor linkage configuration, at least one internal arm and at least one external arm. The antenna includes torsion springs configured to bias the deployable ring towards an open position, with at least one of the torsion springs coupled to one or more of the joints. The antenna includes a plurality of tension, each connecting two joints positioned within the same tier. The antenna includes a flexible reflector mounted on the deployable ring. The flexible reflector includes an upper concave mesh, a lower convex mesh, and connecting flexible rods.