Polysynchronous Satellite Constellation Design
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Solution Overview
Problem
Conventional satellite constellation designs often face challenges such as large coverage gaps and limited opportunities for simultaneous coupled operations, relying on crossing satellite ground tracks for time-sensitive access, which can be inefficient and resilient to failures or environmental effects.
Innovation Solution
A polysynchronous constellation design where multiple spacecraft share a nearly common ground track, with one spacecraft following or leading another, ensuring continuous coverage and resilience by maintaining overlapping coverage, even if one spacecraft is taken out of service.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional satellite constellation designs use crossing ground tracks for coverage, then global coverage can be achieved, but coverage gaps and loss of persistent access occur
Solution Approach 1:
The patent divides the satellite constellation into multiple independent spacecraft, each maintaining its own ground track. By segmenting the constellation into individual satellite units with synchronized orbital parameters, the system achieves continuous coverage through multiple independent contributors rather than relying on crossing tracks, thereby eliminating coverage gaps and maintaining persistent access.
Solution Approach 2:
The patent employs periodic orbital repetitions where satellites follow synchronized ground tracks at regular intervals. By designing orbital parameters that create periodic revisits to the same ground track locations, the system ensures continuous and persistent coverage without gaps, allowing multiple satellites to periodically cover the same areas in a coordinated manner.
2Adaptability or versatility
If satellites operate independently on crossing tracks, then operational flexibility is maintained, but opportunities for simultaneous coupled operations are limited
Solution Approach 1:
The patent implements feedback mechanisms where satellites monitor and communicate their positions, statuses, and operational states to ground control and to each other. This feedback enables ground control to coordinate simultaneous coupled operations by adjusting orbital parameters or operational modes based on real-time information, thereby enhancing adaptability while maintaining operational efficiency through centralized coordination.
Solution Approach 2:
The patent utilizes parameter changes in orbital elements (such as semi-major axis, eccentricity, and inclination) to enable simultaneous coupled operations. By dynamically adjusting these parameters, satellites can be positioned to perform coordinated tasks like interferometry, formation flying, or synchronized observations, thereby achieving versatile coupled operations while maintaining ease of operation through controlled parameter modifications.
3Reliability
If conventional constellations rely on crossing ground tracks, then time-sensitive access is possible, but efficiency and resilience to failures are reduced
Solution Approach 1:
The patent applies beforehand cushioning by designing redundant satellite units that can take over operations if one satellite fails. Each satellite maintains synchronized ground tracks with backup capability, ensuring that operational efficiency is maintained even when individual satellites are taken out of service. This prior cushioning through redundancy enhances resilience without sacrificing productivity.
Solution Approach 2:
The patent implements preliminary action by pre-positioning satellites in synchronized orbits with predetermined ground tracks. This preliminary orbital configuration allows satellites to be ready for immediate coupled operations or failover scenarios, enhancing both resilience to failures and operational efficiency. The pre-established orbital relationships enable quick response to contingencies without disrupting overall constellation productivity.
Data Source
AI summary
Apparatus and methods for determining orbital parameters for spacecraft are provided. A computing device can receive a first plurality of orbital parameters defining a first orbit by a first spacecraft of a particular object. The first orbit can have a corresponding first ground track over the particular object. The computing device can receive a following time for a second spacecraft. The computing device can determine a second plurality of orbital parameters for a second orbit by the second spacecraft of the particular object based on the first plurality of orbital parameters and the following time. The second orbit can have a corresponding second ground track over the particular object that follows the first ground track. The computing device can generate an output that includes the second plurality of orbital parameters.