Distributed Satellite Array for Large Aperture Weight Reduction
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Solution Overview
Problem
The deployment of large antenna structures in space is hindered by high costs and weight due to the need for heavy, expensive components, and existing monolithic satellites are limited in size and efficiency, making it difficult to achieve high throughput and direct connectivity with low-power end user devices.
Innovation Solution
A distributed aperture system using an array of small or very small satellites coordinated to act as a large aperture, eliminating the need for pre-fabricated structures and leveraging electromagnetic forces and natural orbit forces for positioning, allowing for a drastic reduction in weight and cost while increasing antenna efficiency and bandwidth reuse.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of stationary object
If large antenna structures are deployed in space using monolithic satellites, then aperture size and signal effectiveness are improved, but weight and cost increase drastically
Solution Approach 1:
The patent divides a large antenna aperture into multiple smaller satellite elements that operate collectively as a phased array. Instead of launching one large monolithic satellite with a huge antenna, the system uses many small satellites (e.g., 100+ CubeSats) distributed in formation, where each satellite contributes a small antenna element. The combined aperture area of all elements creates the equivalent of a large antenna without the weight of a single large structure.
Solution Approach 2:
The patent transitions from a two-dimensional planar antenna structure to a three-dimensional distributed spatial array. The satellite elements are positioned in three-dimensional space around the target area, creating a volumetric aperture configuration. This allows the system to achieve large effective aperture area while keeping individual satellite components small and lightweight, utilizing spatial distribution rather than planar expansion.
2Measurement precision
If large antenna structures are deployed in space, then signal directionality and receiving effectiveness are improved, but manufacturing complexity and launch requirements increase
Solution Approach 1:
The complex large antenna structure is segmented into multiple simple satellite units, each with basic antenna elements. The complexity is shifted from individual components to the collective arrangement and coordination of many simple units. Each satellite is relatively simple to manufacture, but their coordinated operation in formation creates the complex directional beamforming capability.
Solution Approach 2:
The patent replaces mechanical structural complexity with electromagnetic field coordination. Instead of using complex mechanical positioning mechanisms and rigid support structures to achieve precise antenna geometry, the system uses software-controlled phase and amplitude modulation of radio signals from each satellite element. The desired beam directionality is achieved through signal processing rather than mechanical structure.
3Productivity
If monolithic satellites with large apertures are used, then throughput capability is improved, but power requirements and component weight increase
Solution Approach 1:
The power requirements for high throughput are segmented and distributed across many small satellites rather than concentrated in one large satellite. Each small satellite consumes relatively little power, but their combined signal transmission and reception capabilities achieve the same or greater total throughput. The power load is divided into many small independent units.
Solution Approach 2:
The patent merges the communication capabilities of multiple low-power satellite transmitters to achieve high throughput. By coordinating the signals from many small satellites using phased array beamforming, the system combines their individual low-power transmissions into focused high-gain beams toward target areas, achieving high effective throughput without requiring any single satellite to have high power output.
4Weight of moving object
If distributed satellite arrays are used instead of monolithic satellites, then cost and weight are reduced, but coordination complexity and positioning precision requirements increase
Solution Approach 1:
The patent employs dynamic formation flying where satellite positions and orientations are continuously adjusted in orbit to maintain the desired aperture configuration. Rather than requiring extremely precise static positioning at launch, the system uses active control to dynamically maintain relative positions. Satellites can compensate for orbital perturbations and positioning errors through continuous small adjustments, making the system robust to initial positioning inaccuracies.
Solution Approach 2:
The system uses feedback from GPS and other navigation systems to continuously monitor satellite positions and make real-time corrections. Each satellite's position and orientation is measured, and control commands are sent to adjust thrusters or reaction wheels to maintain the required formation geometry. This closed-loop control allows the system to achieve precise relative positioning despite variations in launch conditions and orbital dynamics.
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 approach results in a significant reduction in satellite weight and cost, enabling high throughput capabilities with large apertures, reduced power requirements, and efficient spectrum reuse, allowing direct connectivity to end user devices without the need for additional antennas or tracking systems.
Implementation Method 1
Satellites can be partially connected or structurally unconnected and keep in close proximity using electromagnetic forces, solar forces and other natural orbit related forces
Implementation Method 2
Satellites can be partially connected or structurally unconnected and keep in close proximity using electromagnetic forces, solar forces and other natural orbit related forces
Implementation Method 3
LEO satellites generate prodigious Doppler at the edge of their field-of-view (FOV) depending on their velocity and the carrier frequency
Data Source
AI summary
A high throughput fractionated satellite (HTFS) system and method where the functional capabilities of a conventional monolithic spacecraft are distributed across many small or very small satellites and a central command and relay satellite, the satellites are separated and flight in carefully design formations that allows the creation of very large aperture or apertures in space drastically reducing cost and weight and enabling high throughput capabilities by spatially reuse spectrum.