Foldable Hemispherical AESA for Rapid Mobile Satcom Deployment
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Solution Overview
Problem
Conventional satellite communication terminals are heavy, cumbersome, and require significant time to assemble, limiting their effectiveness in mobile and tactical operations, especially in war theaters where speed and undetectability are crucial.
Innovation Solution
A mobile satellite communications terminal apparatus featuring an active electronically scanned array (AESA) with stowed and deployed configurations, allowing rapid deployment and configuration for geostationary, middle earth orbit, and low earth orbit operations, including electromechanically steerable subarray panels and a hemispherical field of view.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of time
If conventional satellite terminals are used, then satellite communication capability is achieved, but deployment time is excessive (30 minutes) and weight is high
Solution Approach 1:
The AESA is divided into multiple subarray panels that can be independently folded and stored. Each subarray panel contains multiple tiles with antenna elements, allowing the system to be segmented for compact storage while rapidly deployed when needed, significantly reducing deployment time from 30 minutes to under 2 minutes.
Solution Approach 2:
The side panels and apex panels are designed to fold nested against each other in a compact configuration for transport. The hexagonal subarray panels nest within the folded structure, enabling the entire AESA to be stored in a space-efficient manner on mobile platforms while maintaining full functionality when deployed.
2Ease of operation
If conventional satellite terminals are used, then satellite communication capability is achieved, but mobility and undetectability are compromised
Solution Approach 1:
The AESA incorporates electromechanical pivot joints that enable dynamic reconfiguration between stowed and deployed states. The side panels can pivot relative to the base panel, and apex panels can pivot relative to side panels, allowing rapid transition from a compact transport configuration to a fully deployed hemispherical array, enabling mobility without sacrificing communication capability.
3Reliability
If narrow bandwidth antennas are used, then satellite link is maintained, but power consumption increases due to motion control system
Solution Approach 1:
The AESA employs electronically steerable beamforming capabilities that allow the system to change beam direction and focus electronically without mechanical motion. By controlling the phase and amplitude of signals across multiple antenna elements, the system can track satellites and maintain links through electronic parameter changes rather than physical antenna movement, dramatically reducing power consumption.
4Reliability
If inflatable radome is used, then satellite link is protected, but deployment time increases and wind loading vulnerability occurs
Solution Approach 1:
The patent replaces the inflatable radome mechanical system with a rigid, foldable panel structure that provides equivalent protection. The hexagonal subarray panels and side panels form a rigid framework that protects the antenna elements while eliminating the need for inflation mechanisms, reducing deployment time and eliminating wind loading vulnerabilities associated with inflatable structures.
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 rapid satellite connectivity within minutes, supporting both comms-on-the-move and comms-on-the-halt operations with minimal deployment time, and compatibility with multiple satellite constellations, enhancing mobility and security.
Implementation Method 1
Each subarray panel may be individually configured via an array controller for electromechanically steerable transmission and reception of electromagnetic (EM) radiation at a selectable frequency or polarization
Implementation Method 2
one or more subarray panels may be protected by a dielectric ballistic material. Alternatively, the satcom terminal apparatus may include a radome covering and protecting the AESA subarray panels
Data Source
AI summary
A satellite communications (satcom) terminal apparatus includes an active electronically scanned array (AESA) having stowed and deployed configurations and attachable atop a mobile platform or other flat surface. The AESA comprises a set of panels, each panel a subarray of AESA elements. A set of side panels are attached to a flat surface and an apex panel attached to the top edge of each side panel. When stowed, the apex and side panels lie flat (e.g., for geostationary earth orbit (GEO) operations). When deployed, the side panels and apex panel form a truncated pyramid with a hemispherical field of view for middle earth orbit (MEO) or low earth orbit (LEO) operations. The side panels may be pivoted to any desired slant angle and each subarray panel configured for transmission or reception of electromagnetic energy at a desired frequency or polarization, enabling simultaneous mobile operations with multiple satellites or constellations.