Combined Orbit and Attitude Determination System
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Solution Overview
Problem
Current spacecraft systems require separate and costly subsystems for orbit and attitude determination, which are labor-intensive and unreliable, especially when relying on GPS, leading to high development and operational costs.
Innovation Solution
A combined orbit and attitude determination system using a star sensor, object sensor, and computation module that estimates separation angle, position, and attitude errors, providing a plug-and-play solution independent of GPS and specific sensor designs, allowing simultaneous measurement and calculation of spacecraft position and attitude.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If separate orbit and attitude determination subsystems are used, then measurement precision is maintained, but device complexity and cost increase
Solution Approach 1:
The patent combines separate orbit determination and attitude determination subsystems into a single integrated system. The computation module processes measurements from both star sensor (for attitude) and object sensor (for orbit position) within one unified framework, simultaneously estimating both orbit and attitude parameters. This merging reduces device complexity and eliminates redundant hardware while maintaining measurement precision through coordinated processing of multiple sensor inputs.
Solution Approach 2:
The integrated computation module serves multiple functions: it processes star sensor measurements for attitude determination, object sensor measurements for orbit determination, and performs data fusion to simultaneously determine both orbit and attitude. This multi-functional approach eliminates the need for separate dedicated processing units for each function, reducing overall system complexity while maintaining the precision of individual measurement functions.
2Ease of operation
If GPS-dependent systems are used, then position determination is simplified, but reliability deteriorates
Solution Approach 1:
The patent introduces star-based reference frames as an intermediary for position and attitude determination. Instead of relying on GPS satellites, the system uses stars as natural reference points that are always available in space. The star sensor and object sensor both reference stellar positions, providing a reliable alternative to GPS that works independently of Earth-based satellite systems, thereby improving reliability while maintaining operational simplicity through consistent reference frame usage.
3Measurement precision
If separate processing modules are used for orbit and attitude, then measurement accuracy is maintained, but weight and cost increase
Solution Approach 1:
The computation module merges the processing functions for both orbit and attitude determination into a single integrated unit. This unified module receives inputs from both the star sensor (providing attitude information) and the object sensor (providing orbit position information), and simultaneously computes both orbit and attitude parameters. By consolidating processing functions, the system reduces overall weight while maintaining the measurement accuracy that would otherwise require separate dedicated processing modules.
Data Source
AI summary
A system and methods for calculating an attitude and a position of an object in space are disclosed. Measurements in relation to an object, stars, and a signal timing are received at a combined orbit and attitude determination system to provide received measurements. An estimated separation angle error, an estimated position error, and an estimated attitude error are estimated based upon the received measurements to provide estimated errors.