Satellite Constellation Orbital Configuration for Collision Avoidance
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Solution Overview
Problem
As satellite constellations in non-geosynchronous orbits grow larger, the risk of endogenous collisions increases due to reduced spacing and increased orbital intersections, making traditional collision mitigation techniques infeasible, and this poses challenges for maintaining stable orbits and reducing propellant consumption.
Innovation Solution
The implementation of a system that defines a set of reference orbits with unique combinations of orbital parameters, such as eccentricity and argument of perigee, to create inherent altitude separation among satellites, reducing the risk of collisions and minimizing propellant consumption through precise maneuvering based on sensor data and orbital mechanics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If satellite constellations in non-geosynchronous orbits grow larger, then communication coverage and capacity are improved, but the risk of endogenous collisions increases due to reduced spacing and increased orbital intersections
Solution Approach 1:
The patent introduces a new dimension to orbital separation by utilizing different orbital planes with distinct inclinations and right ascensions of ascending nodes. Satellites are arranged in multiple orbital planes rather than a single plane, creating vertical separation in three-dimensional space. This dimensional approach allows increased constellation size while maintaining safe spacing, as satellites in different planes do not share the same orbital intersection paths, thereby reducing endogenous collision risk while preserving communication capacity.
Solution Approach 2:
The patent segments the satellite constellation into multiple distinct orbital planes, each with unique orbital parameters. By dividing the constellation into separate planar groups with different inclinations and node orientations, the system reduces orbital intersections between satellites. This segmentation strategy enables larger constellation sizes without proportionally increasing collision risk, as each segment operates in its own spatial envelope with minimal overlap.
2Reliability
If traditional collision mitigation techniques are used, then collision risk is reduced, but they become infeasible as constellations grow larger
Solution Approach 1:
The patent applies preliminary action by pre-configuring satellites into specific orbital planes with carefully selected orbital parameters before deployment. The orbital architecture is designed in advance to inherently avoid intersections, eliminating the need for complex real-time collision mitigation systems. This preliminary orbital design approach scales effectively with constellation size, as the collision avoidance is built into the fundamental orbital structure rather than requiring active management.
3Reliability
If satellites maneuver frequently to maintain orbital configuration, then collision risk is reduced, but propellant consumption increases
Solution Approach 1:
The patent creates an equipotential orbital architecture where satellites are positioned in orbital planes that are dynamically balanced to maintain stable configurations over time. By selecting orbital parameters that create natural gravitational balance and minimize perturbations, the system reduces the need for active maneuvering to maintain orbital integrity. This equipotential design allows long-term orbital stability with minimal propellant consumption, as satellites remain in their configured planes without requiring frequent corrective maneuvers.
Data Source
AI summary
A constellation of many satellites are actively maneuvered to maintain specified non-geosynchronous reference orbits. Each satellite is assigned a slot within a particular reference orbit. For each reference orbit, a set of orbital parameters including eccentricity and argument of perigee for frozen orbits are selected that are unique relative to other reference orbits in use. One characteristic of a frozen orbit is that at a given point in the orbit, altitude is relatively constant. At points where orbital planes of the reference orbits intersect, the differing sets of orbital parameters assure a vertical separation between satellites in different orbital planes is maintained without the need for evasive maneuvers. Actual orbital motion data is obtained from sensors onboard each satellite. The desired orbital parameters are maintained based on the actual orbital motion data as part of scheduled maneuvers to maintain the reference orbit assigned to that satellite.