Spacecraft Reentry Prediction Module Using Public Trajectory Data
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Solution Overview
Problem
Current early warning systems for spacecraft reentry are inefficient due to the need for complex and proprietary data, limiting their accuracy and availability, particularly in predicting reentry times for large satellites, which can impact populated areas.
Innovation Solution
A high-efficiency module using simplified inputs and publicly available trajectory information to predict spacecraft reentry times, employing low-order dynamics and environmental models, and integrating equations to simulate reentry trajectories without requiring precise design configurations or aerodynamic data.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If current early warning systems use complex proprietary data and precise atmospheric inputs, then measurement precision of reentry time is improved, but device complexity and cost increase significantly
Solution Approach 1:
The patent replaces expensive, complex proprietary atmospheric data with free, publicly available atmospheric models. The system uses simplified atmospheric density models that can be easily implemented without requiring access to classified or proprietary data, thereby reducing system complexity and cost while maintaining adequate prediction accuracy
Solution Approach 2:
The patent transforms the approach by changing from using precise, complex atmospheric parameters to using simplified atmospheric density models with standard parameters. This parameter simplification reduces the computational burden and system complexity while still providing reliable reentry time predictions
2Measurement precision
If current systems require proprietary data not publicly available, then measurement precision is improved, but ease of operation deteriorates as system becomes inaccessible to public
Solution Approach 1:
The patent creates a public-accessible version of reentry prediction by copying the essential functionality using publicly available data sources. Instead of requiring access to proprietary military or government data, the system replicates the prediction capability using open-source atmospheric models and publicly observable satellite trajectory data
Solution Approach 2:
The patent makes the system universally accessible by designing it to work with publicly available information that anyone can access. The system serves multiple users simultaneously without requiring individual access to restricted data, thereby improving ease of operation and public accessibility
3Measurement precision
If complex methodologies are used, then measurement precision is improved, but productivity decreases as event window shortens to hours or days
Solution Approach 1:
The patent enables preliminary prediction of reentry times much earlier than current systems. By using simplified atmospheric models and public data, the system can make accurate predictions weeks or months in advance, rather than only hours or days before reentry, thereby extending the productive event window for early warning
4Device complexity
If current systems use simplified inputs, then device complexity is reduced, but measurement precision deteriorates due to lack of accurate aerodynamic data
Solution Approach 1:
The patent enables the system to self-correct and improve accuracy over time by using publicly available trajectory information and observational data. The system automatically refines its predictions by comparing predicted vs. actual positions, eliminating the need for complex proprietary aerodynamic data while maintaining or improving precision
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 more accurate and earlier reentry time predictions using publicly available data, making the system more accessible and cost-effective, with predictions possible at least five days in advance.
Implementation Method 1
determining a reentry time of the spacecraft based on a drag coefficient and an atmospheric density model
Data Source
AI summary
The present invention relates to an early warning reentry system comprising a high efficiency module for determining spacecraft reentry time and a highly efficient method for determining spacecraft reentry time. The method permits more accurate, earlier spacecraft reentry time determinations using publicly available trajectory information without the need for accounting for the actual design configuration of the spacecraft in question. Thus, a module for making such determinations can easily and inexpensively be added to an early warning reentry system.