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Comprehensive In-orbit Performance Evaluation of Quantum Sensors for Future Satellite Gravity Missions and Space Navigation

Alireza HosseiniArani, Manuel Schilling, Quentin Beaufils, Annike Knabe, Benjamin Tennstedt, Alexey Kupriyanov, Steffen Schön, Franck Pereira dos Santos, Jürgen Müller

Published Sep 4, 2024• 0 citations
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Recent advances in cold atom interferometry have cleared the path for space applications of quantum inertial sensors, whose level of stability is expected to increase dramatically with the longer interrogation times accessible in space. In this study, an in-orbit model is developed for a Mach-Zehnder-type cold-atom accelerometer. Performance tests are realized under different assumptions about the positioning and rotation compensation method, and the impact of various sources of errors on instrument stability is evaluated. Current and future advances for space-based atom interferometry are discussed, and their impact on the performance of quantum sensors on-board satellite gravity missions is investigated in three different scenarios: state-of-the-art scenario(expected to be ready to launch in 5 years), near-future (expected to be launched in the next 10 to 15 years)and far-future scenarios (expected for the next 20 to 25 years). Our results indicate that the highest sensitivity is achievable by positioning the electrostatic accelerometer at the center of mass of the satellite and the quantum accelerometer aside, on the cross-track axis of the satellite. We show that one can achieve a sensitivity level close to 5×10-10m/s2/Hz with the current state-of-the-art technology. We also estimate that in the near and far-future, atom interferometry in space is expected to achieve sensitivity levels of 1×10-11m/s2/Hz and 1×10-12m/s2/Hz, respectively. A roadmap for improvements in atom interferometry is provided that would maximize the performance of future quantum accelerometers, considering their technical capabilities. Finally, the possibility and challenges of having ultra-sensitive atom interferometry in space for future space missions are discussed.

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Performance Evaluation of Quantum Accelerometers for Space Navigation

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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 10–3Hz, 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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Recent advances in cold atom interferometry have cleared the path for space applications of quantum inertial sensors, whose level of stability is expected to increase dramatically with the longer interrogation times accessible in space. In this study, an in-orbit model is developed for a Mach-Zehnder-type cold-atom accelerometer. Performance tests are realized under different assumptions about the positioning and rotation compensation method, and the impact of various sources of errors on instrument stability is evaluated. Current and future advances for space-based atom interferometry are discussed, and their impact on the performance of quantum sensors on-board satellite gravity missions is investigated in three different scenarios: state-of-the-art scenario(expected to be ready to launch in 5 years), near-future (expected to be launched in the next 10 to 15 years)and far-future scenarios (expected for the next 20 to 25 years). Our results indicate that the highest sensitivity is achievable by positioning the electrostatic accelerometer at the center of mass of the satellite and the quantum accelerometer aside, on the cross-track axis of the satellite. We show that one can achieve a sensitivity level close to 5×10-10m/s2/Hz with the current state-of-the-art technology. We also estimate that in the near and far-future, atom interferometry in space is expected to achieve sensitivity levels of 1×10-11m/s2/Hz and 1×10-12m/s2/Hz, respectively. A roadmap for improvements in atom interferometry is provided that would maximize the performance of future quantum accelerometers, considering their technical capabilities. Finally, the possibility and challenges of having ultra-sensitive atom interferometry in space for future space missions are discussed.
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 10–3Hz, 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.