Deployable LPDA Antenna Membranes for Compact Space Launch
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Solution Overview
Problem
Log-periodic dipole array (LPDA) antennas are historically limited for space applications due to their large size and weight, making them unsuitable for launch vehicles and prone to damage from gravitational forces and vibrations.
Innovation Solution
A deployable antenna system using flexible membranes and extendable support structures that can be stowed in a compact form for launch and expand to a larger size in space, featuring a deployment mechanism with axial and radial support structures to unfurl and tense the membranes, allowing for efficient electromagnetic radiation transmission and reception.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If rigid LPDA antenna structures are used, then antenna performance is maintained, but weight and size increase making them unsuitable for launch vehicles
Solution Approach 1:
The patent applies dynamics by transitioning the antenna from a static rigid structure to a dynamic deployable structure. The antenna elements are configured to be stowed in a compact configuration during launch and then deployed to the operational configuration in space, allowing the same structure to adapt its form factor based on mission phase while maintaining performance when deployed
Solution Approach 2:
The patent implements nesting by stowing the antenna elements in a compact nested configuration during launch. The dipole elements and support structures are arranged to fit within a small volume, similar to nested dolls, and then unfolded to their full operational size in space, achieving both compact stowage and full performance
2Reliability
If rigid LPDA antenna structures are used, then antenna functionality is ensured, but susceptibility to damage from gravitational forces and vibrations increases
Solution Approach 1:
The patent uses dynamics to allow the antenna structure to flex and adapt during launch vibrations and gravitational forces. The deployable configuration enables the structure to absorb mechanical stresses during launch without permanent damage, then achieve its rigid operational form in the space environment where it needs to maintain precise geometry for functionality
Solution Approach 2:
The patent applies beforehand cushioning by designing the deployable structure to absorb and dissipate launch vibrations and gravitational forces during the stowed phase. The flexible stowed configuration acts as a cushion against harmful mechanical forces, protecting the antenna elements before they are deployed to their operational configuration
3Reliability
If large LPDA antenna structures are used, then electromagnetic radiation transmission is effective, but volume increases exceeding launch vehicle specifications
Solution Approach 1:
The patent applies dynamics by making the antenna volume variable rather than fixed. The antenna is stowed in a compact small-volume configuration for launch and then dynamically deployed to the large-volume operational configuration needed for effective electromagnetic radiation transmission in space, adapting its volume to mission requirements
Data Source
AI summary
A deployable antenna system for deployment in an extraterrestrial environment is provided, the deployable antenna system comprising a deployment mechanism including one or more extendable support structures comprising at least one axial support structure adapted to extend in a z-direction parallel to a z-axis in the deployable antenna system and a deployable antenna attached to the one or more extendable support structures and adapted to be stowed in an undeployed state and to be unfurled into a deployed state by the deployment mechanism, the deployable antenna being further adapted to extend and unfurl during deployment from the deployment mechanism in the z-direction responsive to extension of the at least one axial support structure, the deployable antenna including one or more flexible membranes coupled to the at least one axial support structure and extending from the z-axis in the deployed state.