Space Structure Assembly via Electromagnetic Formation Flight
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Solution Overview
Problem
Current space structures, such as large phased-array antennas, face challenges in being launched in a compact stowed configuration due to their size, making them difficult to fit within launch vehicles, and require efficient assembly methods in space to achieve operational configurations.
Innovation Solution
The use of Electro-Magnetic Formation Flight (EMFF) systems and algorithms for the assembly of distributed structures in space, where elements with coils generate magnetic fields to create forces and torques, allowing for automated assembly from a stowed to a deployed configuration without propellant, using a central planning algorithm and onboard software layers for precise control and navigation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of moving object
If large phased-array antennas are deployed in their operational configuration, then their utility and gain increase, but they become too large to fit within launch vehicles
Solution Approach 1:
The antenna is divided into multiple independent modular elements that can be launched separately and then assembled in space. Each element contains its own power source, processing capabilities, and electromagnetic coils, allowing them to be individually controlled during assembly to form the large distributed structure.
Solution Approach 2:
The patent transitions from traditional three-dimensional rigid structures to a distributed configuration where elements are arranged in space using electromagnetic forces. This allows the antenna to achieve its operational area through spatial distribution rather than traditional mechanical deployment.
2Shape
If elements are moved apart to form deployed configuration, then the structure achieves operational shape, but the power required to generate forces increases significantly
Solution Approach 1:
The Earth's magnetic field serves as an intermediary that provides a reference for generating forces between elements. By interacting with the Earth's magnetic field, elements can generate translational forces more efficiently than would otherwise be possible, reducing the power required for positioning.
Solution Approach 2:
The system dynamically adjusts current parameters in electromagnetic coils based on the desired formation and real-time positioning requirements. This allows optimization of power consumption by applying current only when and where needed during the assembly process.
3Extent of automation
If automated assembly algorithms are implemented, then assembly complexity is reduced, but measurement and detection precision requirements increase
Solution Approach 1:
The automated assembly system continuously monitors the positions and orientations of elements using onboard sensors and compares them against the desired deployed configuration. Real-time feedback allows the control algorithms to adjust commands to reachers and elements, compensating for measurement uncertainties and achieving precise assembly.
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 the efficient assembly of large structures in space by maintaining proximity between elements, allowing for the deployment of large or awkwardly shaped structures that would otherwise be too large for launch vehicles, and facilitates the creation of complex formations like phased array antennas.
Implementation Method 1
Inter-satellite magnetic forces (Electromagnetic Formation Flight) is used to physically move the structural elements relative to one another. The elements of the distributed structure include coils through which current may be run to generate magnetic fields with various properties.
Implementation Method 2
Because translational forces that can be generated between a current loop and the magnetic field of the Earth are small
Data Source
AI summary
A system includes a satellite assembly. The assembly includes a plurality of satellite devices, where each satellite device includes a processor device, an impulse actuator, and a memory storing instructions. The instructions are executable by the processor device to access a sequence of waypoints. The sequence of waypoints identifies a first waypoint and is associated with formation of a distributed structure including the plurality of satellite devices. The instructions are further executable by the processor device to initiate movement of the satellite device toward the first waypoint at least by initiating activation of the impulse actuator.