Satellite Constellation Control via Ascending Node Drift
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Solution Overview
Problem
The limited on-board fuel supply in satellites restricts the duration of their service, as a significant portion is used for maintaining orbits and instrument orientation, making certain orbital solutions inaccessible due to high fuel costs.
Innovation Solution
A method where the longitude of the ascending node of each satellite is continuously or pseudo-continuously calculated and regulated to a setpoint equal to the average value, allowing satellites to drift while maintaining service, reducing fuel consumption by leveraging the simultaneous presence of multiple satellites to relay services and monitor overall average secular drift.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If satellites maintain their respective initial orbits precisely, then service coverage and reliability are ensured, but fuel consumption increases significantly
Solution Approach 1:
The patent merges the control of multiple satellites into a coordinated system where satellites can substitute for each other. When one satellite drifts from its nominal orbit, other satellites in the constellation can compensate to maintain service coverage, allowing individual satellites to consume less fuel for orbit maintenance.
Solution Approach 2:
The patent changes the orbital parameters of satellites dynamically. Instead of maintaining fixed nominal orbits, satellites are allowed to drift within acceptable ranges, and their orbital parameters (longitude of ascending node, inclination) are adjusted periodically based on the average drift of the constellation, reducing the frequency and magnitude of fuel-consuming correction maneuvers.
2Weight of moving object
If fuel quantity on board is reduced for lighter satellite design, then launch cost and complexity decrease, but operational duration is limited
Solution Approach 1:
By merging multiple satellites into a functional constellation, the system achieves redundancy and mutual support. This allows each satellite to carry less fuel while the collective constellation maintains the required service duration through satellite substitution and coordinated operations.
Solution Approach 2:
The patent introduces dynamic orbital management where satellites can change their orbital parameters and roles over time. This dynamic approach allows the system to adapt to fuel consumption patterns and extend operational life by optimizing the use of remaining resources across the constellation.
3Manufacturing precision
If trajectory correction maneuvers are performed frequently, then orbital precision is maintained, but service interruptions increase
Solution Approach 1:
Instead of continuous or frequent trajectory corrections, the patent implements periodic correction maneuvers based on the average drift of the satellite constellation. Corrections are performed at optimized intervals when satellites are less critical for service provision, minimizing service interruptions while maintaining acceptable orbital precision.
Solution Approach 2:
The patent makes the satellite constellation universally functional, where any satellite can potentially provide the required service. This multi-functionality allows the system to tolerate larger orbital deviations and perform corrections during periods when other satellites are covering the service requirements.
Data Source
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AI summary
The invention relates to a method of controlling a set of at least two satellites adapted to provide a service implemented by at least a part of the set of said satellites at a given time, in which, continuously or pseudo-continuously, an average value (ΩM(t)) of the longitudes (Ωi(t)) of the respective ascending nodes of each satellite is calculated, and for each satellite, a trajectory correction of the satellite is commanded by regulating the longitude of the ascending node (Ωi(t)) on a setpoint equal to said current average value (ΩM(t)).