Satellite Orbit Propagation via Fuel-Based Velocity Compensation

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Solution Overview

Problem

Existing satellite orbit determination and prediction methods face challenges in accuracy due to insufficient data length and noise errors, leading to inaccurate velocity increment estimation and orbit propagation during station-keeping maneuvers.

Innovation Solution

A flight dynamics subsystem (FDS) that calculates the difference between planned and actual fuel quantities used in a satellite, and compensates the velocity increment error to improve orbit prediction accuracy by using a fuel quantity calculation unit and error calculation unit, incorporating ranging data, angle observation data, and telemetry data.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If the predicted velocity increment from station-keeping maneuver plan is applied directly to orbit propagation, then the process is simple, but the orbit prediction accuracy deteriorates due to large errors in actual maneuver

Engineering Contradiction:

Improvesimplicity of orbit propagation processVSAvoidorbit prediction accuracy

Core Design Contradiction:

Ease of manufactureVSMeasurement precision

Solution Approach 1:

The patent applies feedback by calculating the difference between predicted velocity increment and actual velocity increment from fuel consumption data, then using this error to compensate future predicted velocity increments. This closed-loop feedback mechanism progressively improves orbit prediction accuracy while maintaining computational efficiency.

Inventive Principle:

Principle #23Feedback

Solution Approach 2:

The patent performs preliminary calculation of velocity increment error using fuel consumption data from previous maneuvers, and applies this error compensation in advance to improve the accuracy of subsequent orbit predictions before actual maneuvers occur.

Inventive Principle:

Principle #10Preliminary action

2Productivity

If observation data length is short, then data processing is faster, but velocity increment estimation accuracy deteriorates due to insufficient data

Engineering Contradiction:

Improvedata processing speedVSAvoidvelocity increment estimation accuracy

Core Design Contradiction:

ProductivityVSMeasurement precision

Solution Approach 1:

The patent introduces fuel consumption data as an intermediary parameter that bridges the gap between limited observation data and accurate velocity increment estimation. By using fuel consumption as a mediator, the system can accurately estimate velocity increments even with short observation data lengths.

Inventive Principle:

Principle #24Intermediary (Mediator)

3Measurement precision

If noise filtering is applied to improve velocity increment estimation, then estimation accuracy improves, but processing complexity and time increase

Engineering Contradiction:

Improvevelocity increment estimation accuracyVSAvoidprocessing complexity

Core Design Contradiction:

Measurement precisionVSDevice complexity

Solution Approach 1:

The patent replaces complex noise filtering and data processing mechanisms with a simpler fuel consumption-based calculation approach. By substituting the mechanical/data-intensive estimation process with a physics-based fuel consumption model, accuracy is maintained while processing complexity is reduced.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Data Source

PatentUS8600676B2Method for fast and precise orbit propogation including maneuver

Publication Date: 2013.12.03 ELECTRONICS & TELECOMM RES INST

AI summary

A flight dynamics subsystem (FDS), a velocity increment calculation module, and operational methods of the same are provided. A used fuel quantity actually used in a satellite is calculated, and a velocity increment is calculated using the calculated fuel quantity. Therefore, an orbit of the satellite may be estimated more accurately.