Fractionated Satellite Distributed Aperture for Large Antenna Weight Reduction
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Solution Overview
Problem
Current satellite communication systems face challenges in deploying large antenna structures in space due to increased cost and weight, as well as the need for robust structures to withstand launch accelerations.
Innovation Solution
A high throughput fractionated satellite (HTFS) system that distributes the functional capabilities of a conventional monolithic spacecraft across many small or very small satellites and a central command and relay satellite, forming a distributed aperture system that eliminates the need for a pre-fabricated structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of stationary object
If large antenna structures are deployed in space, then aperture size and signal effectiveness are improved, but weight and cost drastically increase
Solution Approach 1:
The patent divides a conventional monolithic satellite into multiple fractionated satellites (small satellites or cubesats) that form a distributed aperture system. Each satellite carries a small antenna element, and collectively they create a large virtual aperture through coordinated signal processing, eliminating the need for a single large physical antenna structure.
Solution Approach 2:
The patent replaces the mechanical structure of a large physical antenna with a distributed array of small satellites using electromagnetic coordination. Instead of mechanically supporting a large aperture structure, the system uses signal processing and orbital mechanics to create the equivalent of a large antenna aperture virtually.
2Area of stationary object
If large antenna structures are deployed in space, then aperture size and signal effectiveness are improved, but cost drastically increases
Solution Approach 1:
The patent segments the satellite system into multiple small, standardized fractionated satellites that can be manufactured using conventional, cost-effective processes. This allows parallel production and reduces the cost burden compared to building a single complex large-aperture satellite.
Solution Approach 2:
The patent changes the scale parameters from one large satellite to many small satellites, transforming the manufacturing approach from high-cost custom fabrication to lower-cost standardized production, thereby reducing overall system cost while maintaining or improving aperture performance.
3Strength
If pre-fabricated structures are used to withstand launch accelerations, then structural strength is improved, but weight and complexity increase
Solution Approach 1:
The patent divides the system into multiple small satellites that each use simple, lightweight structures sufficient for their individual launch vehicles. The distributed architecture eliminates the need for a single heavy structure designed to withstand extreme launch accelerations, as each small satellite can be optimized for its specific launch profile.
Solution Approach 2:
The patent employs dynamic formation flying where satellites adjust their positions and orientations during and after launch. This dynamic approach allows lightweight structures to achieve the required structural integrity through active control rather than heavy passive reinforcement.
4Power
If payload power requirements increase, then end user terminal connectivity is improved, but weight and cost of power handling components increase
Solution Approach 1:
The patent merges the power capabilities of multiple fractionated satellites to achieve the total payload power required for end user terminal connectivity. Instead of concentrating all power requirements in a single satellite, the distributed system combines the power output of multiple smaller satellites, reducing the power handling burden on each individual platform.
Solution Approach 2:
The patent segments the power system into multiple distributed power sources across fractionated satellites, each with smaller, lighter power handling components. The collective power output meets the required connectivity needs while avoiding the weight penalty of a single large power system.
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 HTFS system achieves a drastic reduction in weight and cost, enables the creation of very large apertures in space, and improves antenna efficiency and bandwidth reuse, allowing for direct connectivity to end user devices without the need for additional infrastructure.
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
The aperture generally refers to the area of an antenna and relates to the ability of the antenna to receive and transmit signals
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.