Deployable Horn Antenna With Biased Hinges for CubeSat Volume Limits
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Solution Overview
Problem
Small satellites, particularly CubeSats, face challenges in implementing compact and deployable antennas for L-band and S-band frequencies due to size constraints, as high-performance antennas require significant volume, making it difficult to fit them within the limited space of these miniaturized satellites.
Innovation Solution
A deployable antenna system comprising a waveguide antenna feed section and a horn antenna section, connected by biased hinges and covered with a flexible electrically conductive layer, which can transition from a collapsed to an extended configuration, allowing for compact storage and efficient deployment in space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a horn antenna is used for L-band and S-band frequencies, then good directivity and low SWR are achieved, but the antenna requires significant volume making it difficult to fit on small satellites
Solution Approach 1:
The horn antenna is divided into multiple deployable sections that can be collapsed into a compact configuration for launch and then extended to the full operational size once in orbit. This segmentation allows the antenna to achieve its required large volume for good performance only when needed, while maintaining a small stowed volume for space-constrained launch vehicles.
Solution Approach 2:
The antenna transitions from a static compact structure to a dynamic deployable structure. Biased hinges and spring mechanisms enable the antenna to automatically transition between stowed and deployed configurations, providing the necessary large volume for L-band and S-band operation while minimizing volume during launch.
2Volume of stationary object
If antenna size is reduced to fit small satellites, then volume constraints are satisfied, but signal loss increases and performance deteriorates
Solution Approach 1:
The antenna is pre-configured with biased hinges and spring mechanisms that automatically activate upon deployment. This preliminary preparation ensures that when the antenna is deployed, it quickly achieves its full operational size and shape, minimizing signal loss and maintaining performance without requiring complex active control systems during the transition.
Solution Approach 2:
The antenna structure changes its physical parameters (size, shape, surface area) from a compact stowed configuration to a fully extended operational configuration. This parameter change allows the antenna to achieve the necessary dimensions for low signal loss at L-band and S-band frequencies only when deployed, while maintaining a small volume during launch.
3Volume of stationary object
If a deployable mechanism is added to reduce stowed volume, then launch volume is reduced, but device complexity increases
Solution Approach 1:
The deployment mechanism uses biased hinges and spring elements that provide automatic self-deployment capability. Once triggered, the mechanism uses its own stored mechanical energy to extend the antenna sections without requiring external actuators, motors, or complex control systems, thereby minimizing added complexity while achieving compact stowed volume.
Solution Approach 2:
Complex electrical actuators and motorized deployment systems are replaced with passive mechanical elements such as biased hinges and spring mechanisms. This substitution reduces the complexity of the deployment mechanism while still achieving the desired compact stowed volume and reliable deployment functionality.
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 provides a lightweight, high-power handling, low-volume antenna with simple deployment mechanisms, suitable for small satellites, capable of operating across a wide frequency range from 0.1 to 18 GHz, with minimal signal loss and the ability to be used for various communication applications.
Implementation Method 1
a first plurality of biased hinges coupling the first plurality of wires together to be self-biased to move between a collapsed stored configuration and an extended deployed configuration
Data Source
Figure 1
Figure 2~5
Figure 5A
AI summary
An outer space deployable antenna may include a waveguide antenna feed section. A first plurality of wires and a first plurality of biased hinges may couple the first plurality of wires together to be self-biased to move between a collapsed stored configuration and an extended deployed configuration. A horn antenna section may be coupled to the waveguide antenna feed section and may include a second plurality of wires and a second plurality of biased hinges coupling the second plurality of wires together to be self-biased to move between the collapsed stored configuration and the extended deployed configuration. A flexible electrically conductive layer may cover the waveguide antenna feed section and the horn antenna section in at least the extended deployed configuration.