Deployable Membrane Antenna Surface for Space Orientation Control
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Solution Overview
Problem
Satellite systems with rotating or spinning structures face challenges in orientation control due to significant moments and imbalances, and existing deployable antenna systems are cumbersome, heavy, and expensive, making them impractical for space applications.
Innovation Solution
A deployable radiofrequency antenna system using a lightweight membrane lens with bi-stable tapes for deployment, which can rotate to sweep a wide observation swath and is designed to be compact and efficient, incorporating actuators and distributed control devices for precise orientation and phase-shifting of radiofrequency energy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional heavy rigid trussing systems are used to support the antenna reflector, then structural strength and stability are improved, but system weight and cost increase significantly
Solution Approach 1:
The patent replaces traditional rigid trussing structures with a flexible membrane that serves as both the structural support and the antenna reflector surface. The membrane is tensioned using deployable struts and cables, creating a lightweight yet structurally sound system that maintains the required shape and stability for radiofrequency operation while dramatically reducing weight compared to rigid alternatives.
Solution Approach 2:
The patent employs composite material structures combining the membrane material with the support strut system. The membrane itself is designed as a composite structure that provides both structural integrity and electromagnetic reflection properties, optimizing the balance between strength and weight.
2Volume of moving object
If the antenna system is deployed in orbit with limited weight and volume specifications, then launch constraints are satisfied, but the available mass for actuating structures is reduced
Solution Approach 1:
The patent employs a dynamically deployable structure that transitions from a compact stowed configuration during launch to a fully deployed operational configuration in orbit. The membrane structure is designed to be inflated or tensioned after deployment, allowing the system to achieve its full functional size while maintaining a small launch footprint. This dynamic transformation resolves the conflict between launch volume constraints and operational structure size.
Solution Approach 2:
The antenna system is divided into modular segments including the membrane panels, support struts, and actuation mechanisms. This segmentation allows each component to be optimized independently for both compact packaging and functional performance, reducing the overall complexity of the actuating structures while satisfying launch constraints.
3Area of stationary object
If the electromagnetic radiation directing surface is made deployable from the satellite body, then the observation swath coverage is improved, but the orientation control becomes more difficult
Solution Approach 1:
The patent incorporates feedback control mechanisms that sense the position and orientation of the deployable membrane surface and adjust the actuation forces accordingly. This closed-loop control system maintains precise orientation of the antenna surface relative to the satellite body and target, compensating for disturbances and ensuring accurate beam pointing despite the flexibility and deployability of the structure.
Data Source
AI summary
A deployable electromagnetic radiation antenna system for extraterrestrial deployment of an electromagnetic radiation directing surface, the deployable electromagnetic radiation antenna system comprising is provided. The deployable electromagnetic radiation antenna system includes one or more deployable support structures, an electromagnetic radiation directing surface, a plurality of actuators, each coupled to one or more of the one or more deployable support structures and the electromagnetic radiation directing surface, and a satellite body, wherein the electromagnetic radiation directing surface is coupled to the satellite body by the one or more deployable support structures and the electromagnetic radiation directing surface is deployable from the satellite body by the one or more deployable support structures.