Shape Memory Composite Antenna for Compact Spacecraft Deployment
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Solution Overview
Problem
Conventional stowable antennas require large areas for RF signal collection, which is challenging for compact spacecraft designs, as they need to maintain performance while being compact and lightweight, and existing inflatable structures add weight and complexity for deployment.
Innovation Solution
The use of shape memory composite materials in a support structure and reflector surface allows for a compact stowed configuration that deploys to a larger configuration, using a flexible membrane with a reflective coating and a deployable framework that releases stored strain energy for expansion, enabling efficient RF signal collection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If conventional stowable antennas use pre-formed rigid structures with discrete positions, then the antenna can be folded into a collapsed configuration, but the structure requires additional components and static pre-formed shapes that increase device complexity
Solution Approach 1:
The patent applies parameter changes by utilizing shape memory materials that can transition between different physical states (stowed and deployed configurations). The support structure changes its geometric parameters dynamically through shape memory effect, eliminating the need for discrete hinges and locking mechanisms while maintaining compact stowage capability.
Solution Approach 2:
The patent employs composite materials, specifically shape memory alloys or polymers, in the support structure to achieve both compactness and deployability. These composite materials provide the necessary mechanical properties to fold into a small volume while maintaining structural integrity during deployment, reducing overall device complexity.
2Adaptability or versatility
If inflatable structures are used for stowable antennas, then no static pre-formed shape is required, but additional components for storing and applying inflation gas are needed, increasing weight and complexity
Solution Approach 1:
The patent extracts the inflation system from the antenna structure by using shape memory materials that inherently provide the deployment mechanism. This removes the need for separate gas storage tanks, valves, and inflation piping, thereby reducing weight while maintaining configuration flexibility.
Solution Approach 2:
The shape memory support structure is self-deploying through its material properties, requiring no external inflation system. The material automatically transitions from stowed to deployed configuration through controlled activation (such as thermal or mechanical stimulus), making the system self-sufficient and eliminating additional weight-bearing components.
3Weight of moving object
If the antenna area is reduced for compact spacecraft, then the spacecraft size and weight decrease, but the sensitivity and resolution of radar antenna detection deteriorate
Solution Approach 1:
The patent applies dynamics by designing an antenna that transitions from a compact stowed configuration to a large deployed configuration in space. The support structure dynamically changes its volume and shape using shape memory materials, allowing the antenna to achieve full detection area once deployed, thereby maintaining measurement precision while enabling compact spacecraft design.
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
This design allows for a compact, lightweight antenna that can deploy to a larger size for effective RF signal collection, maintaining high antenna gain and efficiency while minimizing mass and complexity, suitable for small satellite applications.
Implementation Method 1
The use of shape memory composite materials in a support structure and reflector surface allows for a compact stowed configuration that deploys to a larger configuration, using a flexible membrane with a reflective coating and a deployable framework that releases stored strain energy for expansion
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.