The data is provided in csv file format with file names according to the following convention: YYYY-MM-DD_VENQS_data_fileX_ORBIT_Fall_24h YYYY-MM-DD: date of creation of dataset fileX: filetype 1 or 2 (see following tables) ORBIT: orbit scenario ELLIP or CIRC The simulated data is provided for 24h starting on 22.09.2030 12:00 with a 4s sampling intervall. Data formats Filetype 1 This file includes satellite orbit information. Column Title Description 1 MJD [d] Time stamp as Modified Julian Date 2 pos. x [m] x component of satellite position in ECI (i) frame (ICRF) 3 pos. y [m] y component of satellite position in ECI (i) frame (ICRF) 4 pos. z [m] z component of satellite position in ECI (i) frame (ICRF) 5 vel. x [m/s] x component of satellite velocity in ECI (i) frame (ICRF) 6 vel. y [m/s] y component of satellite velocity in ECI (i) frame (ICRF) 7 vel. z [m/s] z component of satellite velocity in ECI (i) frame (ICRF) 8 qs Scalar component of quaternion of satellite altitude 9 q1 1st imaginary part 10 q2 2nd imaginary part 11 q3 3rd imaginary part 12 omega x [rad/s] x-component of angular velocity in the satellite body frame (b) 13 omega y [rad/s] y-component of angular velocity in the satellite body frame (b) 14 omega z [rad/s] z-component of angular velocity in the satellite body frame (b) The provided quaternions transform a vector in ECI frame (i) into satellite body frame (b) Filetype 2 This filetype includes accelerations and gravity gradients data. Column Title Description 1 MJD [d] Time stamp as Modified Julian Date 2 Drag Acc-x [m/s^2] x-component of satellite acceleration due to atmospheric drag 3 Drag Acc-y [m/s^2] y-component of satellite acceleration due to atmospheric drag 4 Drag Acc-z [m/s^2] z-component of satellite acceleration due to atmospheric drag 5 SRP Acc-x [m/s^2] x-component of satellite acceleration due to solar radiation pressure 6 SRP Acc-y [m/s^2] y-component of satellite acceleration due to solar radiation pressure 7 SRP Acc-z [m/s^2] z-component of satellite acceleration due to solar radiation pressure 8 GG-matrix 1,1 [1/s^2] G11 9 GG-matrix 1,2 [1/s^2] G12 10 GG-matrix 1,3 [1/s^2] G13 11 GG-matrix 2,1 [1/s^2] G21 12 GG-matrix 2,2 [1/s^2] G22 13 GG-matrix 2,3 [1/s^2] G23 14 GG-matrix 3,1 [1/s^2] G31 15 GG-matrix 3,2 [1/s^2] G32 16 GG-matrix 3,3 [1/s^2] G33 The accelerations are provided in the satellite sensor frame. The gravity gradient matrix (GG) is defined at the centre of mass of the satellite in satellite body frame (b) with the components Gxy (x:row y:column).

This dataset accompanies the paper CARIOQA Quantum Pathfinder Mission for space weather research published in Geodesy for a Changing Environment - Proceedings of the 2025 IAG Scientific Assembly (DOI: 10.1007/1345_2026_314). The CARIOQA Quantum Pathfinder Mission aims at demonstrating a quantum technology-based accelerometer in space as a precursor for a later deployment onboard a satellite gravimetry mission. A dedicated satellite will be launched for the Pathfinder Mission in the early 2030s to raise the technology level of the required technologies for applications on operational missions. The Phase A study to investigate the feasibility of this mission has concluded and the project will continue into Phase B in October of 2025. We present studies from the Phase A on the relationship between available models of the atmospheric conditions in low Earth orbits and the instrument and satellite design as well as the impact on the development of requirements to fulfil the mission objectives. In addition to the demonstration of the functionality of the quantum accelerometer, the Pathfinder Mission will also provide accelerometer measurements in low Earth orbits for the expected mission lifetime of three years. As a scientific objective of the mission, this dataset will be used to derive parameters like thermosphere density or atmospheric crosswinds.

Definitions For details we refer to the paper to be published in the IAG Proceedings. Orbits The following sun-synchronous orbits are considered in this study CIRC: circular orbit with 500km altitude ELLIP: elliptical orbit between 400km and 700km altitude. Models The software VENQS was used to simulate the orbit of the satellite considering its 3D geometry and models of the satellites environment Atmospheric drag: NRLMSISE-00 (F10.7 = 115, Ap = 13) Solar Radiation Pressure: Point-like sun; eclipse included Gravity field: GGM05C Frames The satellite is controlled to be nadir pointing. The following frames are defined: Satelite body frame x-axis is pointing along track y-axis is normal to orbital plane pointing towards sun z-axis is pointing radial outward Sensor Frame x-axis is pointing along track y-axis is normal to orbital plane pointing away from sun z-axis nadir pointing