Space Telescope In-Orbit Calibration via Piezo Actuation
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Solution Overview
Problem
Current space telescopes face challenges in accurately calibrating their focus in space due to insufficient accuracy of the Attitude and Orbit Control System and the need to compensate for thermal conditions, which are typically designed for specific orbits and calibrated under Earth's gravity.
Innovation Solution
A space telescope design featuring a primary mirror, secondary mirror, image field corrector, focal plane with optical sensors, and actuating units, including piezo elements, allows for precise adjustments of the focal plane and secondary mirror in multiple directions, ensuring reproducible adjustments of less than 1 nm per pixel, enabling recalibration in space and maintaining consistent imaging quality over the telescope's lifetime.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If calibration is performed under Earth's gravity, then calibration procedures can be simplified, but the calibration accuracy is insufficient for space operations
Solution Approach 1:
The patent changes the physical environment parameter from Earth's gravity to microgravity space conditions, enabling accurate calibration of the telescope's optical system in its actual operating environment. This eliminates the need for complex gravity compensation and ensures calibration accuracy relevant to space operations.
Solution Approach 2:
The telescope system performs self-calibration using its own optical components and sensors in space, without requiring external calibration equipment or ground-based support. The system utilizes its primary mirror, secondary mirror, and optical sensors to conduct calibration procedures autonomously.
2Reliability
If the Attitude and Orbit Control System is used for tracking, then the telescope can maintain orientation, but drifts occur that affect calibration accuracy
Solution Approach 1:
The patent implements feedback mechanisms where the evaluation unit continuously monitors optical sensor data and adjusts the actuating units to compensate for drifts in the Attitude and Orbit Control System. This closed-loop control ensures maintained calibration accuracy despite system dynamics.
Solution Approach 2:
The system dynamically adjusts the focus and position of optical components using actuating units that respond to real-time feedback from optical sensors. This dynamic adjustment capability allows the system to compensate for drifts and maintain optimal calibration throughout operation.
3Adaptability or versatility
If thermal conditions are designed for a specific orbit, then the telescope structure is optimized, but thermal variations affect calibration stability
Solution Approach 1:
The patent compensates for thermal effects by dynamically adjusting optical parameters such as focus position and mirror alignment using actuating units. This allows the system to adapt to thermal variations while maintaining calibration stability, decoupling the thermal design optimization from calibration performance.
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 allows for accurate calibration and recalibration of space telescopes in space, ensuring consistent imaging quality by adjusting the focus and compensating for drifts, thereby maintaining optimal performance despite environmental changes and system inaccuracies.
Implementation Method 1
The actuating units preferably comprise piezo actuating elements, by means of which readjustment can be carried out with high accuracy
Data Source
AI summary
A space telescope comprising a primary mirror, a secondary mirror, an image field corrector, a focal plane with at least one optical sensor and an evaluation unit for the data from the optical sensor, the focal plane being assigned at least one actuating unit, the at least one actuating unit being designed to displace the focal plane in the X- and Y-directions, the secondary mirror being assigned at least one further actuating unit, the at least one further actuating unit being designed to displace the secondary mirror in the Z-direction, the actuating unit further being designed to ensure a reproducible adjustment of at least 1 nm over at least one pixel length of the optical sensor, with the Z-direction being parallel to the optical axis of the space telescope, and to a method for calibrating a space telescope in space.