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Performance Evaluation of Quantum Accelerometers for Space Navigation

Publikation: Beitrag in Buch/Bericht/Sammelwerk/KonferenzbandAufsatz in KonferenzbandForschungPeer-Review

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  • Technische Universität München (TUM)

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OriginalspracheEnglisch
Titel des Sammelwerks2024 DGON Inertial Sensors and Applications, ISA 2024
Herausgeber/-innenPeter Hecker
Herausgeber (Verlag)Institute of Electrical and Electronics Engineers Inc.
Auflage2024
ISBN (elektronisch)9798350387513
PublikationsstatusVeröffentlicht - 22 Okt. 2024
Veranstaltung2024 International Conference on DGON Inertial Sensors and Applications, ISA 2024 - Braunschweig, Deutschland
Dauer: 22 Okt. 202423 Okt. 2024

Abstract

Inertial navigation is an essential technology for space applications due to its autonomy from external signals and references. In space, inertial navigation systems utilize accelerometers and gyroscopes to measure changes in velocity and orientation, enabling a spacecraft to determine its trajectory independently, assuming the gravitational accelerations are well known. While conventional accelerometers onboard space missions often suffer from a large drift in the frequency range below 10-3 Hz, quantum accelerometers can provide highly stable and drift-free measurements of non-gravitational acceleration and consequently improve the spacecraft orbits. This work evaluates the performance of a 3-axis quantum accelerometer for space navigation. In this paper, we analyze the performance of such sensors onboard a spacecraft in a parking orbit around Earth in two scenarios of maintaining a nadir-looking orientation and having an inertially fixed spacecraft. To achieve this goal, we simulate a spacecraft in the low Earth orbit using gravitational and non-gravitational accelerations, and we develop an in-orbit performance model for Mach- Zehnder-type quantum accelerometers capable of calculating the detection noise, quantum projection noise, laser frequency noise, wavefront aberration bias, and contrast loss, together with external effects such as the impact of rotation, and gravity gradient for each individual measurement. Using this modeling and based on the propagated orbit, we simulate the measurements of a 3-axis quantum accelerometer along the orbit in two different scenarios: first, we assume the spacecraft to maintain a nadir-pointing orientation, and then we consider another scenario in which the spacecraft is assumed to be inertially- fixed. The results demonstrate that the nadir-pointing orientation introduces more noise, particularly in the along-track and radial directions, due to uncompensated rotation. However, in both the nadir-pointing and inertially fixed scenarios, quantum sensors still produce white noise, consistent with their drift-free measurement capabilities. Furthermore, the findings emphasize the critical role of sensor placement within the spacecraft. Positioning the quantum accelerometer along the main axis of rotation is optimal, as it reduces the impact of centrifugal forces and improves measurement accuracy. This is especially important for spacecraft in nadir-pointing orientations or during maneuvers. This research is the simulation and implementation of a low-Earth orbit, undertaken as a proof-of-concept. In the future, we implement this modeling for a trajectory from Earth to the Moon. We discuss the challenges, limitations, and potential solutions.

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Performance Evaluation of Quantum Accelerometers for Space Navigation. / Hosseiniarani, Alireza; Sreekantaiah, Arpetha C.; Tennstedt, Benjamin et al.
2024 DGON Inertial Sensors and Applications, ISA 2024. Hrsg. / Peter Hecker. 2024. Aufl. Institute of Electrical and Electronics Engineers Inc., 2024.

Publikation: Beitrag in Buch/Bericht/Sammelwerk/KonferenzbandAufsatz in KonferenzbandForschungPeer-Review

Hosseiniarani, A, Sreekantaiah, AC, Tennstedt, B, He, X, Hugentobler, U & Schon, S 2024, Performance Evaluation of Quantum Accelerometers for Space Navigation. in P Hecker (Hrsg.), 2024 DGON Inertial Sensors and Applications, ISA 2024. 2024 Aufl., Institute of Electrical and Electronics Engineers Inc., 2024 International Conference on DGON Inertial Sensors and Applications, ISA 2024, Braunschweig, Deutschland, 22 Okt. 2024. https://doi.org/10.1109/ISA62769.2024.10786040
Hosseiniarani, A., Sreekantaiah, A. C., Tennstedt, B., He, X., Hugentobler, U., & Schon, S. (2024). Performance Evaluation of Quantum Accelerometers for Space Navigation. In P. Hecker (Hrsg.), 2024 DGON Inertial Sensors and Applications, ISA 2024 (2024 Aufl.). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/ISA62769.2024.10786040
Hosseiniarani A, Sreekantaiah AC, Tennstedt B, He X, Hugentobler U, Schon S. Performance Evaluation of Quantum Accelerometers for Space Navigation. in Hecker P, Hrsg., 2024 DGON Inertial Sensors and Applications, ISA 2024. 2024 Aufl. Institute of Electrical and Electronics Engineers Inc. 2024 doi: 10.1109/ISA62769.2024.10786040
Hosseiniarani, Alireza ; Sreekantaiah, Arpetha C. ; Tennstedt, Benjamin et al. / Performance Evaluation of Quantum Accelerometers for Space Navigation. 2024 DGON Inertial Sensors and Applications, ISA 2024. Hrsg. / Peter Hecker. 2024. Aufl. Institute of Electrical and Electronics Engineers Inc., 2024.
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title = "Performance Evaluation of Quantum Accelerometers for Space Navigation",
abstract = "Inertial navigation is an essential technology for space applications due to its autonomy from external signals and references. In space, inertial navigation systems utilize accelerometers and gyroscopes to measure changes in velocity and orientation, enabling a spacecraft to determine its trajectory independently, assuming the gravitational accelerations are well known. While conventional accelerometers onboard space missions often suffer from a large drift in the frequency range below 10-3 Hz, quantum accelerometers can provide highly stable and drift-free measurements of non-gravitational acceleration and consequently improve the spacecraft orbits. This work evaluates the performance of a 3-axis quantum accelerometer for space navigation. In this paper, we analyze the performance of such sensors onboard a spacecraft in a parking orbit around Earth in two scenarios of maintaining a nadir-looking orientation and having an inertially fixed spacecraft. To achieve this goal, we simulate a spacecraft in the low Earth orbit using gravitational and non-gravitational accelerations, and we develop an in-orbit performance model for Mach- Zehnder-type quantum accelerometers capable of calculating the detection noise, quantum projection noise, laser frequency noise, wavefront aberration bias, and contrast loss, together with external effects such as the impact of rotation, and gravity gradient for each individual measurement. Using this modeling and based on the propagated orbit, we simulate the measurements of a 3-axis quantum accelerometer along the orbit in two different scenarios: first, we assume the spacecraft to maintain a nadir-pointing orientation, and then we consider another scenario in which the spacecraft is assumed to be inertially- fixed. The results demonstrate that the nadir-pointing orientation introduces more noise, particularly in the along-track and radial directions, due to uncompensated rotation. However, in both the nadir-pointing and inertially fixed scenarios, quantum sensors still produce white noise, consistent with their drift-free measurement capabilities. Furthermore, the findings emphasize the critical role of sensor placement within the spacecraft. Positioning the quantum accelerometer along the main axis of rotation is optimal, as it reduces the impact of centrifugal forces and improves measurement accuracy. This is especially important for spacecraft in nadir-pointing orientations or during maneuvers. This research is the simulation and implementation of a low-Earth orbit, undertaken as a proof-of-concept. In the future, we implement this modeling for a trajectory from Earth to the Moon. We discuss the challenges, limitations, and potential solutions.",
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AU - Hosseiniarani, Alireza

AU - Sreekantaiah, Arpetha C.

AU - Tennstedt, Benjamin

AU - He, Xingchi

AU - Hugentobler, Urs

AU - Schon, Steffen

N1 - Publisher Copyright: © 2024 IEEE.

PY - 2024/10/22

Y1 - 2024/10/22

N2 - Inertial navigation is an essential technology for space applications due to its autonomy from external signals and references. In space, inertial navigation systems utilize accelerometers and gyroscopes to measure changes in velocity and orientation, enabling a spacecraft to determine its trajectory independently, assuming the gravitational accelerations are well known. While conventional accelerometers onboard space missions often suffer from a large drift in the frequency range below 10-3 Hz, quantum accelerometers can provide highly stable and drift-free measurements of non-gravitational acceleration and consequently improve the spacecraft orbits. This work evaluates the performance of a 3-axis quantum accelerometer for space navigation. In this paper, we analyze the performance of such sensors onboard a spacecraft in a parking orbit around Earth in two scenarios of maintaining a nadir-looking orientation and having an inertially fixed spacecraft. To achieve this goal, we simulate a spacecraft in the low Earth orbit using gravitational and non-gravitational accelerations, and we develop an in-orbit performance model for Mach- Zehnder-type quantum accelerometers capable of calculating the detection noise, quantum projection noise, laser frequency noise, wavefront aberration bias, and contrast loss, together with external effects such as the impact of rotation, and gravity gradient for each individual measurement. Using this modeling and based on the propagated orbit, we simulate the measurements of a 3-axis quantum accelerometer along the orbit in two different scenarios: first, we assume the spacecraft to maintain a nadir-pointing orientation, and then we consider another scenario in which the spacecraft is assumed to be inertially- fixed. The results demonstrate that the nadir-pointing orientation introduces more noise, particularly in the along-track and radial directions, due to uncompensated rotation. However, in both the nadir-pointing and inertially fixed scenarios, quantum sensors still produce white noise, consistent with their drift-free measurement capabilities. Furthermore, the findings emphasize the critical role of sensor placement within the spacecraft. Positioning the quantum accelerometer along the main axis of rotation is optimal, as it reduces the impact of centrifugal forces and improves measurement accuracy. This is especially important for spacecraft in nadir-pointing orientations or during maneuvers. This research is the simulation and implementation of a low-Earth orbit, undertaken as a proof-of-concept. In the future, we implement this modeling for a trajectory from Earth to the Moon. We discuss the challenges, limitations, and potential solutions.

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ER -

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