Papers by MANUEL SANJURJO RIVO
Deep Learning Based Target Pose Estimation Using LiDAR Measurements in Active Debris Removal Operations
IEEE Transactions on Aerospace and Electronic Systems, 2023
A Novel Variable Specific Impulse Optimization Methodology for Modulable Electric Propulsion Systems
A Novel Trajectory Concept for a Mission to the Inner Large Moons of Saturn
SSRN Electronic Journal
Iterative Graph Deformation for Aircraft Trajectory Planning Considering Ensemble Forecasting of Thunderstorms
SSRN Electronic Journal
A major challenge for Trajectory-Based Operations is the existence of significant uncertainties i... more A major challenge for Trajectory-Based Operations is the existence of significant uncertainties in the models and systems required for trajectory prediction. In particular, weather uncertainty has been acknowledged as one of the most (if not the most) relevant ones. In the present paper we present preliminary results on robust trajectory planning at the pre-tactical level. The main goal is to plan trajectories that are efficient, yet predictable. State-of-the-art forecasts from Ensemble Prediction Systems are used as input data for the wind field, which we assume to be the unique source of uncertainty. We develop an ad-hoc optimal control methodology to solve trajectory planning problems considering uncertainty in wind fields. A set of Pareto- optimal trajectories is obtained for different preferences between predictability and average efficiency; in particular, we present and discuss results for the minimum average fuel trajectory and the most predictable trajectory, including the ...
Optimization of constellation deployment using on-board propulsion and Earth nodal regression
Advances in Space Research
Satellite maneuver detection and estimation with radar survey observations
Acta Astronautica
CEAS Space Journal
This paper proposes a novel track-to-track association methodology able to detect and catalogue r... more This paper proposes a novel track-to-track association methodology able to detect and catalogue resident space objects (RSOs) from associations of uncorrelated tracks (UCTs) obtained by radar survey sensors. It is a multi-target multi-sensor algorithm approach able to associate data from surveillance sensors to detect and catalogue objects. The association methodology contains a series of steps, each of which reduces the complexity of the combinational problem. The main focus are real operational environments, in which brute-force approaches are computationally unaffordable. The hypotheses are scored in the measurement space by evaluating a figure of merit based on the residuals of the observations. This allows us to filter out most of the false hypotheses that would be present in brute-force approaches, as well as to distinguish between true and false hypotheses. The suitability of the proposed track-to-track association has been assessed with a simulated scenario representative of...
Journal of Propulsion and Power, 2010
Analytical mechanics techniques are applied to the construction of three kite flight simulators w... more Analytical mechanics techniques are applied to the construction of three kite flight simulators with applications to airborne wind energy generation and sport uses. All of themweredevelopedunder aminimal coordinate formulation approach. This choice has the main advantage of yielding a set of ordinary differential equations free of algebraic constraints, a feature that distinguishes the simulators from codes based on classical mechanics formulation and improves their robustness and efficiency.
Correction: Optimal Low-Thrust Orbital Plane Spacing Maneuver for Constellation Deployment and Reconfiguration including J2
AIAA SCITECH 2022 Forum, 2022
This paper describes the main challenges, strategies and methodologies found during the build-up ... more This paper describes the main challenges, strategies and methodologies found during the build-up and maintenance of a catalogue of (resident space objects) RSOs: a robust automated database containing information of every detected object. It does not only characterise the properties of the objects, but also provides precise ephemerides that allow Space Surveillance and Tracking (SST) products generation, including sensor tasking, collision prediction, re-entry prediction and fragmentation detection. Such a catalogue must be built-up and maintained through the processing of observation data from various types of sensors, including radars and telescopes, both ground-based and space-based, as well as satellite laser ranging stations.
Optimal Low-Thrust Orbital Plane Spacing Maneuver for Constellation Deployment and Reconfiguration including J2
AIAA SCITECH 2022 Forum, 2022
This work presents a novel sequential filtering algorithm able to identify new objects from optic... more This work presents a novel sequential filtering algorithm able to identify new objects from optical measurement data by associating uncorrelated tracks (UCTs) belonging to the same object. It makes use of both Initial Orbit Determination (IOD) and Orbit Determination (OD) methods to evaluate a figure of merit to help deciding whether certain tracks belong to the same object or not. Instead of using a brute-force approach by evaluating all possible combinations of UCTs, several filters and complexity reduction techniques are used to reduce the computational resources required. Furthermore, the association is performed on the measurements space (track-to-track correlation) rather than in the orbit space (track-to-orbit or orbit-to-orbit correlation). A generic object detection methodology based on track association is presented, with a special emphasis on the correlation of optical tracks, although it has been already applied to correlation of radar tracks. In the former case, the pro...
The large increase in the amount of debris orbiting our planet has become a problem for present a... more The large increase in the amount of debris orbiting our planet has become a problem for present and future space missions. Space debris is mainly composed of inactive satellites, rocket bodies and pieces of both detached by collisions. The number of spacecrafts has grown in a sustained manner since the 1950s and, as a consequence, debris created by fragmentation of large satellites has increased at a very fast rate. Currently, the number of objects resulting from fragmentation duplicates the number of inactive satellites and rockets. Approximately 20,000 pieces of debris larger than a softball (≈ 10 cm) have been catalogued and it is believed that more than 2 million objects with a diameter larger than 2 cm orbit the Earth. Actively tracking all these objects is a very expensive task in terms of time and resources. A method to propagate uncertainties into the future up to a new programmed or expected observation in a reliable way is needed to compensate the lack of continuous tracki...
Desarrollo De Un Simulador De Vuelo Orbital. Estudio De Perturbaciones
Journal of Guidance, Control, and Dynamics, 2017
Celestial Mechanics and Dynamical Astronomy, 2015
The two-body problem subject to a constant radial thrust is analyzed as a planar motion. The desc... more The two-body problem subject to a constant radial thrust is analyzed as a planar motion. The description of the problem is performed in terms of three perturbation methods: DROMO and two others due to Deprit. All of them rely on Hansen's ideal frame concept. An explicit, analytic, closed-form solution is obtained for this problem when the initial orbit is circular (Tsien problem), based on the DROMO special perturbation method, and expressed in terms of elliptic integral functions. The analytical solution to the Tsien problem is later used as a reference to test the numerical performance of various orbit propagation methods, including DROMO and Deprit methods, as well as Cowell and Kustaanheimo-Stiefel methods.
Journal of Aerospace Engineering, Sciences and Applications, 2012
Numerical explorations show how the known periodic solutions of the Hill problem are modified in ... more Numerical explorations show how the known periodic solutions of the Hill problem are modified in the case of the attitude-orbit coupling that may occur for large satellite structures. We focus on the case in which the elongation is the dominant satellite's characteristic and find that a rotating structure may remain with its largest dimension in a plane parallel to the plane of the primaries. In this case, the effect produced by the non-negligible physical length is dynamically equivalent to the perturbation produced by an oblate central body on a mass-point satellite. Based on this, it is demonstrated that the attitude-orbital coupling of a long enough body may change the dynamical characteristics of a periodic orbit about the collinear Lagrangian points.
AIAA/AAS Astrodynamics Specialist Conference and Exhibit, 2008
Electrodynamic tethers (EDT) are a promising alternative for producing the energy required in any... more Electrodynamic tethers (EDT) are a promising alternative for producing the energy required in any scientific exploration mission to Io and its plasma torus, which are generally handcuffed by a scarcity of power. We propose two alternatives using EDT working in the generator regime: 1) a bare self-balanced electrodynamic tether in equilibrium position in the synodic frame Jupiter-Io, and 2) a rotating EDT orbiting around Io to generate permanent power and to provide propellantless orbital maneuvering capability. For the first alternative we derive the necessary orbital and tether design conditions for equilibrium and the system performances in terms of power generation. For the second alternative, we investigate two mission scenarios both involving a 25-km-long 5-cm-wide tape tether placed on a stable retrograde equatorial orbit around Io capable to provide kW-level useful power extracted from the fast rotating Jupiter plasmasphere. In the first scenario the tether current is controlled to provide maximum power generation. The amount of power produced and the impact on the orbit stability is investigated numerically. In the second scenario the current is controlled in order to reduce or increase the orbital energy of the system with the possibility of reaching escape velocity. Results show that EDT can be used as a permanent power production system in exploration missions to Io and the surrounding plasma torus without compromising the orbital stability.
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Papers by MANUEL SANJURJO RIVO