Star Sensor Calibration via Removable Constellation Simulator
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Solution Overview
Problem
The existing method for calibrating star sensors on spacecraft requires a permanently mounted mirror cube, leading to high procurement and assembly costs, increased sensor mass, and complex calibration processes that are time-consuming and not compatible with high production throughput needs, especially for constellation programs.
Innovation Solution
A calibrated constellation simulator that projects a defined star formation onto the star sensor, allowing for calibration without a mirror cube, enabling the user to perform calibration and testing, reducing costs and mass, and allowing for faster production by eliminating the need for complex alignment measurements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a mirror cube is permanently mounted on the star sensor for calibration, then the star sensor can be calibrated to the spacecraft reference system, but the sensor mass increases and procurement and assembly costs increase
Solution Approach 1:
The invention extracts the calibration function from the star sensor itself by removing the permanently mounted mirror cube. Instead, a separate removable calibration unit with its own mirror element is used, which can be detached after calibration. This separates the calibration auxiliary component from the main sensor, reducing the operational mass of the star sensor while maintaining calibration capability.
Solution Approach 2:
The invention introduces a separate calibration unit as an intermediary component between the star sensor and the calibration process. This calibration unit contains the mirror element needed for calibration but is not permanently integrated into the star sensor. The calibration unit serves as a temporary mediator that enables calibration without becoming part of the permanent sensor assembly, thus reducing mass.
2Measurement precision
If a mirror cube is permanently mounted on the star sensor for calibration, then the star sensor can be calibrated to the spacecraft reference system, but procurement and assembly costs increase
Solution Approach 1:
The calibration function is extracted from the main star sensor assembly into a separate, standalone calibration unit. This separation allows the calibration unit to be manufactured independently using simpler, more cost-effective processes. The removable design reduces assembly complexity and enables standardized production of both the star sensor and calibration unit as separate components.
Solution Approach 2:
The calibration system is segmented into a removable calibration unit that can be separately manufactured and assembled. This segmentation allows different teams to manufacture the star sensor and calibration unit independently, enabling parallel production streams and reducing overall procurement and assembly costs while maintaining calibration functionality.
3Measurement precision
If the mirror cube remains permanently mounted on the star sensor, then the calibration reference is available, but the spacecraft mass increases with no operational benefit
Solution Approach 1:
The mirror element is extracted from a permanently mounted configuration and placed in a removable calibration unit. After calibration is completed, the calibration unit can be removed or stowed, eliminating the unnecessary mass from the operational spacecraft configuration while preserving the calibration reference functionality when needed.
Solution Approach 2:
The calibration unit is designed as a temporary component that is used during calibration and then can be discarded or stowed away. The mirror element and associated calibration hardware are recovered (removed) after serving their calibration purpose, eliminating dead weight from the spacecraft while maintaining the ability to perform calibration when required.
4Measurement precision
If the star sensor manufacturer performs the ARF/BRF measurement using a mirror cube, then the calibration can be done, but the calibration process is time-consuming and incompatible with high production throughput
Solution Approach 1:
The calibration unit is designed to enable self-calibration or simplified calibration procedures that do not require complex alignment measurements by the manufacturer. The removable design and integrated mirror element allow for quicker, more straightforward calibration processes that can be performed more rapidly, increasing production throughput while maintaining measurement accuracy.
Solution Approach 2:
The calibration unit is pre-configured with the mirror element and calibration references in a fixed, predetermined arrangement. This preliminary preparation eliminates the need for time-consuming alignment measurements during the calibration process itself, as the geometric relationships are already established during manufacturing. This allows for faster calibration and higher production throughput.
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
This solution reduces manufacturing effort and costs, allows for user-calibration of star sensors, and eliminates the need for a mirror cube, enhancing production throughput and reducing the mass of the star sensor and spacecraft.
Implementation Method 1
an optical device (111) configured to project a defined star formation (IRF) of a star catalog preferably onto a star sensor (120) mounted on a spacecraft (130)
Data Source
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AI summary
The present invention relates to a calibrated star image simulator (110), a system (100), and a method (V) for calibrating and/or testing a star sensor (120) mounted on a spacecraft (130). The calibrated star image simulator (110) comprises an optical device (111) configured to project a defined star formation (IRF) from a star catalog, preferably onto a star sensor (120) mounted on a spacecraft (130). Furthermore, the calibrated star image simulator (110) comprises a calibration unit (113) with a position and/or orientation reference (ARF) of the calibrated star image simulator (110) configured to detect a position and/or orientation of the calibrated star image simulator (110) in space, wherein the defined star formation (IRF) and the position and/or orientation reference (ARF) are in a first fixed calibrated rotation (QOSPS) relative to each other.The calibrated constellation simulator (110) improves the calibration of the star sensor (120) as an independent calibration standard. The constellation simulator (110) becomes a calibration standard.