Multi-Optic Star Tracking for Spacecraft Attitude Under Disturbances
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Solution Overview
Problem
Existing methods for determining the position of a spacecraft in space often rely on gyroscopes, which can be unreliable in high dynamic conditions and are affected by disturbances such as solar flares, leading to inaccurate position and rotation rate measurements.
Innovation Solution
A stellar gyro system using optical sensors with multiple orientations and image processing units to compute position and rotation rates without gyroscopes, employing redundancy and real-time data processing to handle disturbances and high dynamic conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If gyroscopes are used for position determination, then measurement capability is provided, but reliability deteriorates under high dynamic conditions and solar flare disturbances
Solution Approach 1:
The patent replaces the mechanical gyroscope system with an optical measurement system using star sensors. The gyroscope-based mechanical rotation sensing is substituted by optical detection of star field patterns, eliminating the harmful mechanical components that fail under high dynamic conditions and solar flare disturbances.
Solution Approach 2:
The patent introduces an intermediary optical measurement system between the spacecraft and the reference frame. Instead of direct mechanical sensing, optical sensors detect star positions and constellation patterns serve as intermediaries to determine orientation, providing reliability under disturbances that affect direct mechanical sensors.
2Measurement precision
If multiple star sensors with different fields of view are used, then measurement precision is improved, but device complexity increases
Solution Approach 1:
The patent divides the measurement system into multiple independent star sensors, each with specific fields of view covering different portions of the sky. This segmentation allows each sensor to optimize for its specific coverage area while the overall system achieves complete spherical coverage, improving measurement precision without requiring a single overly complex sensor.
Solution Approach 2:
The patent creates a multi-functional sensor system where multiple star sensors serve both individual optimization purposes and collective system functions. The sensors work together to provide comprehensive attitude determination, with each sensor contributing to the overall measurement precision while sharing the common function of spacecraft orientation monitoring.
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
Provides accurate and reliable position and rotation rate information even in high dynamic conditions and under disturbances, reducing the need for gyroscopes and improving system availability.
Implementation Method 1
a sensor system with a plurality of star sensors, each of which detects constellation sections by means of an optical system and a light-sensitive matrix detector
Data Source
AI summary
A method for determining the position of a spacecraft in space includes receiving image data from a plurality of differently oriented optics modules, processing the received image data and computing a position, a rate of rotation and/or direction of rotation from the processed image data. The method may be carried out with the aid of at least one image processing module, a device for carrying out such a method, and a computer program for carrying out such a method on such a device.