Compactable RF membrane antenna
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional stowable antennas require large areas for RF signal collection, which is challenging for compact spacecraft due to the need for a large antenna area while maintaining compact storage and deployment capabilities without adding weight or complexity.
Innovation Solution
The use of a shape memory composite support structure that can collapse and deploy dynamically, allowing for a compact stowed configuration and a larger deployed configuration, utilizing a membrane reflector with a reflective surface and a toroidal ring and struts made of composite materials for high stiffness and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If conventional rigid stowable antennas with discrete hinge positions are used, then the antenna can be folded into a collapsed configuration, but the structure requires pre-formed static shapes and additional deployment components
Solution Approach 1:
The patent applies dynamics by replacing static pre-formed hinge positions with a dynamic continuum mechanism. The flexible support structure allows continuous deformation during deployment, eliminating the need for discrete locked positions and complex deployment mechanisms. The structure transitions smoothly from stowed to deployed configurations through elastic deformation of the flexible material.
Solution Approach 2:
The patent utilizes parameter changes by employing a flexible support structure whose stiffness and shape are dynamically adjusted during deployment. The flexible material undergoes elastic deformation, changing its geometric parameters continuously to achieve both compact stowed and fully deployed configurations without requiring additional deployment components.
2Adaptability or versatility
If inflatable structures are used for stowable antennas, then static pre-formed shapes are not required, but additional space and weight are needed for storing and applying inflation gas
Solution Approach 1:
The patent applies self-service by designing a flexible support structure that automatically transitions from stowed to deployed configurations through elastic deformation. The structure serves its own deployment function without requiring external inflation gas or additional deployment mechanisms, thereby reducing weight while maintaining configuration flexibility.
Solution Approach 2:
The patent replaces the mechanical inflation system with an elastic deformation mechanism. Instead of using gas pressure to achieve deployment, the flexible support structure utilizes its inherent elastic properties to transition between configurations, eliminating the need for heavy inflation systems while maintaining adaptability.
3Area of stationary object
If large antenna area is maintained for RF signal collection, then sensitivity and resolution are improved, but the antenna cannot be compacted for spacecraft storage
Solution Approach 1:
The patent applies segmentation by dividing the large antenna surface into multiple flexible support elements that can be independently deformed. This allows the antenna to be compacted into a small stowed volume while maintaining the capability to expand into a large deployed area for RF signal collection, resolving the contradiction between area and storage volume.
Solution Approach 2:
The patent implements nesting by allowing the flexible support structure to collapse into a compact configuration that fits within the spacecraft payload volume. The same structure then expands to its full deployed area in space, effectively nesting the large antenna area within a small storage volume through reversible elastic deformation.
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
Enables the creation of compactable antennas with reduced storage volume and increased deployed volume, maintaining high antenna gain and efficiency, suitable for small satellites and nanosatellites, while minimizing additional weight and complexity.
Implementation Method 1
The use of a shape memory composite support structure that can collapse and deploy dynamically
Implementation Method 2
a membrane reflector with a reflective surface
Data Source
AI summary
Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.