Rievers, Benny
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Rievers, Benny
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Rievers, Benny
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Item-typ:Veröffentlichung, Carrier-Phase-Based Multi-Vehicle Cooperative Positioning Using V2V SensorsThis work proposes a new cooperative architecture that using Global Navigation Satellite System (GNSS), Inertial Measurement Unit (IMU) and vehicle-to-vehicle (V2V) observations to obtain robust and accurate inter-vehicle state estimation. A new cascade structure of relative filter which consists of float estimator and fixed estimator is presented that can take advantage of both the multi-sensor data and the information from Least-squares ambiguity decorrelation adjustment (LAMBDA). Also, a cooperative baseline estimation method based on multidimensional scaling (MDS) is proposed to further exploit the relative estimation from many other collaborators. Lastly, we combine the cascade relative filter (CRF) with MDS to estimate the relative states cooperatively using a feedback scheme. In the verification part, we use realistic sensor noise and a GNSS signal simulator to obtain inter-vehicle and GNSS measurements for a multiple-vehicle network. In a harsh GNSS scenario, only 51.20% of epochs in RTKLIB software can pass the LAMBDA acceptance test, but our proposed methods can achieve 77.85% (CRF) and 85.05% (CRF/MDS). Referring to the recovery time from a float solution to fixed solution, RTKLIB needs 179.23 s in the case of 4 satellites, but only 34.88 s (CRF) and 21.39 s (CRF/MDS) for the proposed methods. Results show that the proposed CRF has good performance when fusing with IMU and V2V observations, and has a better performance than existing methods. Moreover, the proposed architecture that combines CRF and MDS can have a further improvement, which substantially increases the robustness and accuracy of relative state estimation.Wissenschaftlicher ArtikelBand:69Heft:993 63 - Some of the metrics are blocked by yourconsent settings
Item-typ:Veröffentlichung, Attitude determination & control system design for gravity recovery missions like GRACE(Elsevier, 2020-04-25); ; This paper is dedicated to the attitude control law synthesis for GRACE-like missions. Namely, two satellites move along the same orbit at a distance of several hundred kilometers and “look” at each other. This angular motion resembles the stabilization at unstable equilibrium position in the Orbital Frame. The reaction wheels cannot be used because they greatly affect the accelerometers measurements. Hence, only magnetorquers and thrusters may be utilized for the attitude control. Two different approaches are considered: linear quadratic regulator and Lyapunov-based controller. Control coefficients of the latter are obtained using the Floquet theory. Numerical simulation including atmospheric drag, solar radiation pressure and state vector measurements errors is carried out to validate suggested control techniques. The developed attitude determination and control system algorithms are tested for GRACE and GRACE-FO mission scenarios with relevant requirements and parameters.Wissenschaftlicher ArtikelBand:17347 20 - Some of the metrics are blocked by yourconsent settings
Item-typ:Veröffentlichung, MICROSCOPE instrument description and validation(IOP Publishing, 2022-09-14)58 10 - Some of the metrics are blocked by yourconsent settings
Item-typ:Veröffentlichung, High precision modelling of thermal perturbations with application to Pioneer 10 and Rosetta(2012-01-13); ; ; This thesis deals with the exact numerical determination of thermal recoil pressure (TRP) and solar radiation pressure (SRP) for complex satellite geometries. The basic equations for both perturbations are introduced and expanded into a generic numerical approach based on finite element modeling and ray-tracing. The method is applied to the missions Pioneer 10 and Rosetta. For Pioneer 10, it is found that the so-called Pioneer anomaly can fully be explained by the recoil resulting from anisotropic heat radiation. In case of Rosetta, observed discrepancies of ESAs SRP models are resolved as unmodeled TRP. Furthermore both SRP and TRP are analysed for the first Earth fly-by. Here both effects can be excluded as causes of the observed fly-by anomaly.Dissertation336 206 - Some of the metrics are blocked by yourconsent settings
Item-typ:Veröffentlichung, MICROSCOPE Mission: Final Results of the Test of the Equivalence Principle.(American Physical Society, 2022-09-14)53 44