Initial Orbit Determination Using Angular Rate and Acceleration Data
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current methods for initial orbit determination (IOD) are slow and inaccurate due to the need for lengthy calculations and the coupling of angular velocity and angular acceleration with position measurements, which are prone to errors, especially in dynamic orbital environments with changing parameters.
Innovation Solution
Directly measure angular velocity and angular acceleration using sensors like IPCs and EBCs, decoupling these measurements from position data, and inputting them into new algorithms for rapid and accurate IOD.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If standard orbit determination methods using multiple position measurements are used, then orbit parameters can be determined, but the process takes relatively long time (minutes or hours)
Solution Approach 1:
The patent extracts angular velocity and angular acceleration measurements from the traditional position-based measurement system. By using these derived measurements as additional inputs to the orbit determination algorithm, the system achieves faster convergence without sacrificing accuracy, resolving the contradiction between speed and precision in orbit determination.
Solution Approach 2:
The patent changes the measurement parameters from purely positional data to include angular velocity and angular acceleration data. This parameter transformation enables the orbit determination algorithm to converge faster by providing additional dynamic information about the satellite's motion, thus reducing the time required while maintaining determination accuracy.
2Loss of time
If Laplace method with three discrete observations is used, then initial orbit can be determined quickly, but angular velocity and angular acceleration change dramatically between observations leading to inaccurate estimates
Solution Approach 1:
The patent applies preliminary actions by continuously measuring and tracking angular velocity and angular acceleration throughout the observation period rather than relying on discrete snapshots. This continuous monitoring allows the system to capture the dynamic changes in rotational parameters, enabling accurate orbit determination even when these parameters change significantly over time.
Solution Approach 2:
The patent incorporates feedback mechanisms by using the measured angular velocity and angular acceleration as inputs to iteratively refine the orbit determination. The system continuously updates the orbital parameters based on the measured rotational data, allowing it to adapt to changing conditions and maintain accuracy despite rapid variations in angular parameters.
3Adaptability or versatility
If more satellites are placed into orbit to monitor unconventional orbits, then coverage is improved, but orbital clutter increases and tracking becomes more difficult
Solution Approach 1:
The patent replaces traditional position-based tracking mechanics with a rotational dynamics-based approach. By measuring angular velocity and angular acceleration, the system can distinguish between actual orbital changes and apparent motion caused by observer rotation, simplifying the tracking of multiple satellites even in cluttered orbital environments with unconventional orbits.
Data Source
AI summary
The current disclosure provides systems and methods of directly measuring angular velocity and angular acceleration of space objects and using the measured angular velocity and angular acceleration as inputs into new and unique algorithms for initial orbit determination. Sensors measuring locations and times of light events may be used to generate a virtual rate track image for identification of space objects. Right ascension and declination of the space object events versus time may be fit to polynomials or splines to determine associated angle, angular rate, and angular acceleration of the space objects. New and unique initial orbit algorithms may then be applied to estimate orbital elements of the space objects.